NASA Aeronautical Engineering Aeror sring ... - CORE

NASAAeronautical NASA SP-7037(165)Engineering September 1983A ContinuingBibliographywith Indexes

(fcaSA-SP-7937 ( I t 5 ) ) A _ c C N A U l i C A LE N G I N E E R I N G : A L L ^ I N U I N G t i t L I O G f c A « ? H i tillti

1! It:.) («a t A C i J d lAeronautics and Space Administration) 131 pHC S5.UU CSCL CIA QO/Q 1

National Aeronautics andSpace Administration

25th Anniversary1958-1983

Aeronautical Engineering Aerorsring Aeronautical Engineeringigineering Aeronautical Enginesal Engineering Aeronautical Elautical Engineering AeronautAeronautical Engineering Aerosring Aeronautical Engineeringigineering Aeronautical Enginesal Engineering Aeronautical Elautical Engineering AeronautAeronautical Engineering Aerosring Aeronautical Engineering

https://ntrs.nasa.gov/search.jsp?R=19840001941 2020-03-21T00:32:06+00:00Z

ACCESSION NUMBER RANGES

Accession numbers cited in this Supplement fall within thefollowing ranges.

STAR (N-10000 Series) N83-25651 - N83-27949

IAA (A-10000 Series) A83-33485 - A83-36991

This bibliography was prepared by the NASA Scientific and Technical Information Facilityoperated for the National Aeronautics and Space Administration by PRC Government InformationSystems.

NASASP-7037(165)

AERONAUTICAL ENGINEERING

A CONTINUING BIBLIOGRAPHYWITH INDEXES

(Supplement 165)

A selection of annotated references to unclassifiedreports and journal articles that were introduced intothe NASA scientific and technical informationsystem and announced in August 1983 in

Scientific and Technical Aerospace Reports(STAR)

International Aerospace Abstracts (IA A).

Scientific and Technical Information Branch 1983National Aeronautics and Space Administration

Washington DC

This supplement is available as NTISUB/141/093 from the National Technical Information Service(NTIS), Springfield, Virginia 22161 at the price of $5 00 domestic, $10 00 foreign

INTRODUCTION

Under the terms of an mteragency agreement with the Federal Aviation Administrationthis publication has been prepared by the National Aeronautics and Space Administration forthe joint use of both agencies and the scientific and technical community concerned with thefield of aeronautical engineering The first issue of this bibliography was published inSeptember 1970 and the first supplement in January 1971

This supplement to Aeronautical Engineering -- A Continuing Bibliography (NASA SP-7037) lists 466 reports, journal articles, and other documents originally announced in August1983 in Scientific and Technical Aerospace Reports (STAR) or in International AerospaceAbstracts (IAA)

The coverage includes documents on the engineering and theoretical aspects of design,construction, evaluation, testing, operation, and performance of aircraft (including aircraftengines) and associated components, equipment, and systems It also includes research anddevelopment in aerodynamics, aeronautics, and ground support equipment for aeronauticalvehicles

Each entry in the bibliography consists of a standard bibliographic citation accompaniedin most cases by an abstract The listing of the entries is arranged by the first nine STARspecific categories and the remaining STAR major categories This arrangement offers theuser the most advantageous breakdown for individual objectives The citations, and abstractswhen available, are reproduced exactly as they appeared originally in IAA and STAR,including the original accession numbers from the respective announcement journals The IAAitems will precede the STAR items within each category

Six indexes -- subject, personal author, corporate source, contract number, reportnumber, and accession number -- are included.

An annual cumulative index will be published

in

AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A83-10000 Series)

All publications abstracted in this Section are available from the Technical Information Service,American Institute of Aeronautics and Astronautics, Inc. (AIAA), as follows: Paper copies ofaccessions are available at $8.00 per document. Microfiche0' of documents announced in IAAare available at the rate of $4.00 per microfiche on demand, and at the rate of $1.35 per microfichefor standing orders for all IAA microfiche.

Minimum air-mail postage to foreign countries is $2.50 and all foreign orders are shipped onpayment of pro-forma invoices.

All inquiries and requests should be addressed to AIAA Technical Information Service. Pleaserefer to the accession number when requesting publications.

STAR ENTRIES (N83-10000 Series)

One or more sources from which a document announced in STAR is available to the publicis ordinarily given on the last line of the citation. The most commonly indicated sources andtheir acronyms or abbreviations are listed below. If the publication is available from a sourceother than those listed, the publisher and his address will be displayed on the availability lineor in combination with the corporate source line.

Avail: NTIS. Sold by the National Technical Information Service. Prices for hard copy (HC)and microfiche (MF) are indicated by a price code preceded by the letters HC orMF in the STAR citation. Current values for the price codes are given in the tableson page vii.

Documents on microfiche are designated by a pound sign (#) following the accessionnumber. The pound sign is used without regard to the source or quality of themicrofiche.

Initially distributed microfiche under the NTIS SRIM (Selected Research inMicrofiche) is available at greatly reduced unit prices. For this service and forinformation concerning subscription to NASA printed reports, consult the NTISSubscription Section, Springfield, Va. 22161.

NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (thosefollowed by the * symbol), use the N accession number. NASA patent applications(only the specifications are offered) should be ordered by the US-Patent-Appl-SNnumber. Non-NASA publications (no asterisk) should be ordered by the AD, PB,or other report number shown on the last line of the citation, not by the N accessionnumber. It is also advisable to cite the title and other bibliographic identification.

Avail: SOD (or GPO). Sold by the Superintendent of Documents, U.S. Government PrintingOffice, in hard copy. The current price and order number are given following theavailability line. (NTIS will fill microfiche requests, as indicated above, for thosedocuments identified by a # symbol.)

Avail: NASA Public Document Rooms. Documents so indicated may be examined at orpurchased from the National Aeronautics and Space Administration, PublicDocument Room (Room 126), 600 Independence Ave., S.W., Washington, D.C.20546, or public document rooms located at each of the NASA research centers,the NASA Space Technology Laboratories, and the NASA Pasadena Office at theJet Propulsion Laboratory.

(1) A microfiche is a transparent sheet of film, 105 by 148 mm in size containing as many as 60 to 98 pages of information reducedto micro images (not to exceed 26 1 reduction)

Avail- DOE Depository Libraries Organizations in U S. cities and abroad that maintaincollections of Department of Energy reports, usually in microfiche form, are listedin Energy Research Abstracts Services available from the DOE and its depositoriesare described in a booklet, DOE Technical Information Center - Its Functions andServices (TID-4660), which may be obtained without charge from the DOE TechnicalInformation Center

Avail Univ Microfilms Documents so indicated are dissertations selected fromDissertation Abstracts and are sold by University Microfilms as xerographic copy(HC) and microfilm All requests should cite the author and the Order Number asthey appear in the citation

Avail USGS. Originals of many reports from the U S. Geological Survey, which maycontain color illustrations, or otherwise may not have the quality of illustrationspreserved in the microfiche or facsimile reproduction, may be examined by the publicat the libraries of the USGS field offices whose addresses are listed in thisintroduction The libraries may be queried concerning the availability of specificdocuments and the possible utilization of local copying services, such as colorreproduction

Avail HMSO. Publications of Her Majesty's Stationery Office are sold in the U S. byPendragon House, Inc. (PHI), Redwood City, California The U S price (includinga service and mailing charge) is given, or a conversion table may be obtained fromPHI

Avail BLL (formerly NLL): British Library Lending Division, Boston Spa, Wetherby,Yorkshire, England Photocopies available from this organization at the price shown(If none is given, inquiry should be addressed to the BLL )

Avail: Fachmformationszentrum, Karlsruhe Sold by the FachmformationszentrumEnergie, Physik, Mathematik GMBH, Eggenstem Leopoldshafen, Federal Republicof Germany, at the price shown in deutschmarks (DM)

Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries asto the availability of these documents should be addressed to the organization shownin the citation as the corporate author of the document

Avail U S. Patent and Trademark Office. Sold by Commissioner of Patents andTrademarks, U.S. Patent and Trademark Office, at the standard price of 50 centseach, postage free.

Other availabilities If the publication is available from a source other than the above, thepublisher and his address will be displayed entirely on the availability line or incombination with the corporate author line.

GENERAL AVAILABILITY

All publications abstracted in this bibliography are available to the public through the sourcesas indicated in the category sections It is suggested that the bibliography user contact his ownlibrary or other local libraries prior to ordering any publication inasmuch as many of the documentshave been widely distributed by the issuing agencies, especially NASA. A listing of publiccollections of NASA documents is included on the inside back cover.

ADDRESSES OF ORGANIZATIONS

American Institute of Aeronautics andAstronautics

Technical Information Service555 West 57th Street, 12th FloorNew York, New York 10019

British Library Lending Division,Boston Spa, Wetherby, Yorkshire,England

National Technical Information Service5285 Port Royal RoadSpringfield, Virginia 22161

Pendragon House, Inc.899 Broadway AvenueRedwood City, California 94063

Commissioner of Patents andTrademarks

U.S Patent and Trademark OfficeWashington, D.C. 20231

Superintendent of DocumentsU.S. Government Printing OfficeWashington, D.C. 20402

Department of EnergyTechnical Information CenterP.O. Box 62Oak Ridge, Tennessee 37830

University MicrofilmsA Xerox Company300 North Zeeb RoadAnn Arbor, Michigan 48106

ESA-lnformation Retrieval ServiceESRINVia Galileo Galilei00044 Frascati (Rome) Italy

University Microfilms, LtdTylers GreenLondon, England

Fachmformationszentrum Energie, Physik,Mathematik GMBH

7514 Eggenstein LeopoldshafenFederal Republic of Germany

U.S Geological Survey LibraryNational Center - MS 95012201 Sunrise Valley DriveReston, Virginia 22092

Her Majesty's Stationery OfficeP.O. Box 569, S.E. 1London, England

U.S. Geological Survey Library2255 North Gemini DriveFlagstaff, Arizona 86001

NASA Scientific and Technical InformationFacility

P.O. Box 8757B.W.I. Airport, Maryland 21240

U.S. Geological Survey345 Middlefield RoadMenlo Park, California 94025

National Aeronautics and SpaceAdministration

Scientific and Technical InformationBranch (NIT-41)

Washington, D C. 20546

U.S Geological Survey LibraryBox 25046Denver Federal Center, MS 914Denver, Colorado 80225

VI

NTIS PRICE SCHEDULES

Schedule A

STANDARD PAPER COPY PRICE SCHEDULE

(Effective January 1, 1983)

Prlc*Cod*

A01A02A03A04A05A06

Page Ring*

Microfiche001-025026-050051-075076-100101-125

North AmericanPrlc*

S 450700850

10 0011 501300

ForeignPrlc*

$ 90014001700200023002600

A07A08A09A10A11

126-150151-175176-200201-225226-250

14 5C1600175019002050

290032003500380041 00

A12A13A14A15A16

251-275276-300301-325326-350351-375

22002350250026502800

44004700500053005600

A17

A18A19A20A21

376-400401-425426-450451-475476-500

295031 00325034003550

590062006500680071 00

A22A23A24A25A99

501-525526-550551-575576-600601 -up

37003850400041 50

-1

7400770080008300

•- 2

I/ Add$1 50 for each additional 25 page increment or portion thereof for 601 pagesup

21 Add $3 00 for each additional 25 page increment or portion thereof for 601 pages and more

Schedule E

EXCEPTION PRICE SCHEDULEPaper Copy & Microfiche

Prlc*Cod*E01E02E03E04EOS

North AmtrlcinPrlc.

$ 650750950

11 501350

Foreign

Prlc*

$ 13501550195023502750

E06E07

EOSE09E10

15501750195021 502350

31 503550395043504750

E11E12E13E14E15

2550285031 5034503750

51 505750635069507550

E16E17

E18E19E20

40504350465051 5061 50

81 5088509350

1025012350

E-99 - Write for quote

N01 35 00 4500

VII

TABLE OF CONTENTS

Page

Category 01 Aeronautics (General) 415

Category 02 Aerodynamics 417Includes aerodynamics of bodies, combinations, wings, rotors, and controlsurfaces, and internal flow in ducts and turbomachmery

Category 03 Air Transportation and Safety 428Includes passenger and cargo air transport operations, and aircraft accidents

Category 04 Aircraft Communications and Navigation 430Includes digital and voice communication with aircraft, air navigation systems(satellite and ground based), and air traffic control

Category 05 Aircraft Design, Testing and Performance 433Includes aircraft simulation technology

Category 06 Aircraft Instrumentation 443Includes cockpit and cabin display devices, and flight instruments

Category 07 Aircraft Propulsion and Power 445Includes prime propulsion systems and systems components, e g , gas turbineengines and compressors; and on-board auxiliary power plants for aircraft

Category 08 Aircraft Stability and Control 460Includes aircraft handling qualities; piloting; flight controls, and autopilots

Category 09 Research and Support Facilities (Air) 462Includes airports, hangars and runways; aircraft repair and overhaul facilities;wind tunnels, shock tube facilities; and engine test blocks

Category 10 Astronautics 467Includes astronautics (general); astrodynamics, ground support systems andfacilities (space), launch vehicles and space vehicles; space transportation;spacecraft communications, command and tracking; spacecraft design, testingand performance, spacecraft instrumentation; and spacecraft propulsion andpower.

Category 11 Chemistry and Materials 467Includes chemistry and materials (general), composite materials; inorganicand physical chemistry, metallic materials; nonmetallic materials; andpropellants and fuels

VIII

Category 12 Engineering 472Includes engineering (general), communications, electronics and electricalengineering; fluid mechanics and heat transfer, instrumentation andphotography, lasers and masers, mechanical engineering, quality assuranceand reliability, and structural mechanics

Category 13 Geosciences 479Includes geosciences (general); earth resources, energy production andconversion, environment pollution, geophysics, meteorology and climatology,and oceanography

Category 14 Life Sciences N.A.Includes sciences (general); aerospace medicine, behavioral sciences; man/system technology and life support, and planetary biology

Category 15 Mathematics and Computer Sciences 480Includes mathematical and computer sciences (general); computer operationsand hardware, computer programming and software, computer systems;cybernetics, numerical analysis, statistics and probability, systems analysis,and theoretical mathematics

Category 16 Physics 481Includes physics (general), acoustics; atomic and molecular physics; nuclearand high-energy physics; optics, plasma physics; solid-state physics, andthermodynamics and statistical physics

Category 17 Social Sciences 484Includes social sciences (general), administration and management,documentation and information science, economics and cost analysis, law andpolitical science, and urban technology and transportation

Category 18 Space Sciences N.A.Includes space sciences (general), astronomy, astrophysics, lunar andplanetary exploration, solar physics, and space radiation

Category 19 General 487

Subject Index A-1Personal Author Index B-1Corporate Source Index C-1Contract Number Index D-1Report Number Index E-1Accession Number Index F-1

IX

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSOREDDOCUMENT

NASA ACCESSIONNUMBER

TITLE

AUTHOR-

CONTRACTOR GRANT-

REPORTNUMBER—

-*-N«3-l106r# Applied inst of Mathematics, Inc.. Evanston, Ill •«—-*A NONLINEAR STRUCTURAL CONCEPT FOR COMPLIANT

WALLS Final Report-»•£. l_ REISS Washington NASA Oct 1982^40 p refs-•-(Contract NAS1 -14717) ^

r—(NASA-CR-3628, NAS 1 26 3628) Avail NTIS HC A03/MF A01*CSCL 01 A-

Two mechanisms of drag reduction for flow over flat plateswere investigated The first mecnanism employs BushneH'shypothesis that compliant walls produce drag reduction byinterfering witn the formation of the turbulent spots in a turbulentboundary layer It is shown that the amplitudes and frequenciesof compliant wall motions for drag reduction might be achievedby using slightly curved walls and the resulting large amplitudemotions of snap bucxling. A simple structural model of an arch isused in the analysis, and an asymptotic method a developed.The required wall motions can be obtained by using materials likemylar In addition, the delay of transition from laminar to turbulentflow by driven walls was studied for Poiseuille channel flow Thewalls are driven by a periodic traveling wave A s.gmficant increasein the 'ransitional Reynolds number .s ob'amea oy aopropnatelypresobing the wavelength and phase velocity of the wall motionP'sviously developed asymptotic methods are used in theanalysis M G.

-AVAILABLE ONMICROFICHE

-CORPORATESOURCE

-PUBLICATIONDATE

-AVAILABILITYSOURCE

-COSATICODE

TYPICAL CITATION AND ABSTRACT FROM IAA

AIAA ACCESSIONNUMBER

AUTHOR

TITLE OFPERIODICAL-

LIFE DEVELOPMENTAIRCRAFT

Of COMPONENTS/SYSTEMS OF-

R OUGGAL (Indian Airlines. Bombay, lndia)̂ .Aeronautical Societyof India Journal, vol. 33. Fab.-May 198J. p. 35-39.

Three aspects of a maintenance program am described. Thefirst, referred to here as hard time limit (HTL). involves the removaland complete overhaul of an aircraft component at fixed timeintervals. A second type of maintenance procedure, referred to as'on condition,' is used with parts that are allowed to remain inservice until there is a failure, suspected failure, or scheduledinspection The third type of procedure is called conditionmonitonng This is used on items that are neither overhauled norinspected on a regular basis. The unit or part is operated untilfailure occurs. Economies in maintenance can be achieved by aludioous combination of these procedures. C R.

-AVAILABLE ONMICROFICHE

-TITLE

AFFILIATION

-PUBLICATIONDATE

AERONAUTICALENGINEERING A Continuing Bibliography (Suppl. 165)

SEPTEMBER 1983

01

AERONAUTICS (GENERAL)

A83-33622A COMPLETE INTRODUCTION TO THE REVOLUTIONARY NEWWAY TO FLY ULTRALIGHTSJ E MRAZEK, JR and J E MRAZEK, SR New York, StMartin's Press, 1982, 204 p

The various materials, construction and piloting techniques,configurations, and uses of ultralight aircraft, which do not requirepilot's license to fly, are explored Attention is given to the evolutionof the ultralight aircraft from hang gliders based on the Rogallowing, and to the categories of ultralights, including their propulsionsystems The control systems are described, together with thenecessary equipment, instrumentation, and maintenanceprocedures Flight theory is reviewed, as is flying instruction forultralights Meteorological conditions significant to ultralight pilotsare examined, as are uses of ultralights as glider tows, for militarymissions, and as amphibious aircraft National and internationalprograms, clubs, and other activities involving ultralight aircraft aresummarized M S K

A83-36203FLIGHT SIMULATION TECHNOLOGIES CONFERENCE,NIAGARA FALLS, NY, JUNE 13-15, 1983, COLLECTION OFTECHNICAL PAPERSConference sponsored by the American Institute of Aeronauticsand Astronautics New York, American Institute of Aeronauticsand Astronautics, 1983, 174 p

The present conference on flight simulation technologiesconsiders the indoctrination of U S Navy test pilots in vectoredthrust practices by means of the X-22A in-flight simulator, theimprovement of flight performance simulator fidelity in the B-52HWST flight station simulator, advanced display techniques for thetraining of multimember tactical air crews, a visual cueing modelfor terrain following applications, and the spectral decontaminationof real time helicopter simulations Also discussed are benchmarksfor a computer system for NASA's Space Shuttle ProceduresSimulator, error sources in hybrid computer-based flight simulation,simulator performance definition by cue synchronization analysis,NASA's new Man-Vehicle Systems Research Facility, and theapplication of experimentally derived pilot perceptual angularresponse transfer functions O C

A83-36443AIRCRAFT PRODUCTION TECHNOLOGY (2ND REVISED ANDENLARGED EDITION) [TEKHNOLOGIIA SAMOLETOSTROENIIA/2ND REVISED AND ENLARGED EDITION/]A L ABIBOV, N M BIRIUKOV, V V BOITSOV, V P GRIGOREV,I A ZERNOV, P F CHUDAREV, and A I IARKOVETS Moscow,Izdatel'stvo Mashmostroenie, 1982, 552 p In Russian refs

This textbook on aircraft fabrication and production reflectsrecent technological advances both inside and outside the USSRThe principles underlying aircraft production technology areexamined, with particular attention given to quality control, cost

efficiency of fabrication, and techniques of mechanization andautomation Processes for the fabrication of aircraft parts, assemblyprocesses, and the assembly of aircraft control systems andequipment are considered in detail B J

A83-36457AIRCRAFT PROTOTYPE AND TECHNOLOGY DEMONSTRATORSYMPOSIUM, DAYTON, OH, MARCH 23, 24, 1983,PROCEEDINGSSymposium sponsored by the American Institute of Aeronauticsand Astronautics New York, American Institute of Aeronauticsand Astronautics, 1983, 196 p

The present conference on aircraft prototype programmanagement and technology demonstrator development considersthe course from technology development to operational stagesfor the B-36, B-58, x and F-111/FB-111 aircraft, the technologyadvancements incorporated into the XB-70 aircraft's design, thedevelopment of variable sweep wing design from the Bell X-5 tothe F-14, the application of low cost demonstrators to the evaluationof advanced fighter technology, and gas turbine engine prototypedevelopment practices Also discussed are the YAV-8B flightdemonstrator program, the AFTI/F-111 Mission Adaptive Wingdevelopment program, Highly Maneuverable Aircraft technologydevelopment, the testing of a low altitude 'night-in-weather' attacksystem, the development history of the Northrop 'Flying Wing'prototypes, and the development history of the F-5 fighter O C

A83-36458#PROTOTYPING FOR FUN AND PROFITM D MARKS (McDonnell Douglas Corp, St Louis, MO) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 1-7(AIAA PAPER 83-1045)

Attention is given to the prototype program experiences gainedin the course of developing such experimental and military servicesdesign competition aircraft as the XP-85 'parasite fighter', the XP-88supersonic fighter prototype, and the subsequently highlysuccessful F4H-1 Phantom, of which more than 5000 wereproduced Prototype development and testing experiences are alsorelated for the cases of the XHJD-1 twin engine/twin rotorhelicopter and the HV-1 and HV-3 advanced rotary wind conceptdemonstrator aircraft OC

A83-36459#FROM NEW TECHNOLOGY DEVELOPMENT TO OPERATIONALUSEFULNESS B-36, B-58, F-111/FB-111F E ARMSTRONG (General Dynamics Corp, Fort Worth, TX)IN Aircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 9-17(AIA PAPER 83-1046)

While the B-36, B-58 and F-111 weapon systems all achievedsuperior performance through the selective use of advancedtechnology to meet demanding requirements, a number ofretrospectively interesting technologies developed and tested inconnection with these programs never reached the operationalphase Cases in point are the track landing gear developed forthe B-36 prototype, which could not withstand landing loads, andthe use of the B-36 as a mother aircraft for F-84F reconnaissance

415

01 AERONAUTICS (GENERAL)

fighters and as nuclear reactor test bed Attention is given to thevariety of F-111 variants O C

A83-36471#THE NORTHROP FLYING WING PROTOTYPESL BEGIN (Northrop Corp, Aircraft Div, Hawthorne, CA) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 135-144(AIAA PAPER 83-1047)

The evolution of the Northrop Flying Wing prototypes isdescribed with attention given to preliminary design work in the1920's, the evolution through several prototype stages beginningwith the N-1M in 1939, the development of the N-9M series asone-third scale prototypes for a projected long-range bomber, thefirst flight of the XB-35 in June 1946, and the 1947 flight of theYB-49 Consideration is also given to such prototypes as the XP-56Black Bullet, a fighter/interceptor, the XP-79B Flying Ram, theMX-324/MX-334, prototypes for a rocket-powered interceptor, andthe X-4 Skylancer, a Flying Wing research vehicle built to studyhigh subsonic stability and control phenomena The XT-37Turbodyne engine program, involving the first turboprop qualifiedfor flight in the United States, is also considered B J

A83-36914#DYNAMICS OF AIR COMBATW B HERBST (Messerschmitt-Boelkow-Blohm GmbH, Munich,West Germany) (Israel Annual Conference on Aviation andAstronautics, 24th, Tel Aviv and Haifa, Israel, February 17, 18,1982, Collection of Papers) Journal of Aircraft (ISSN 0021-8669),vol 20, July 1983, p 594-598

Previously cited in issue 07, p 862, Accession no A83-21026

A83-36960THE FUTURE OF THE MANNED AIRCRAFTM LAMBERT Interavia (ISSN 0020-5168), vol 38, June 1983,p 581-593

After assessing the prospects for manned aircraft systemdevelopments from the present to the year 2000 and beyond,with attention to longterm requirements being formulated forpayload capacity, fuel consumption and life cycle costs in thevarious passenger, cargo and military aircraft categories, a seriesof detailed aircraft system element considerations is presentedThese concern laminar flow techniques, advanced fighter design,airliner and business aircraft, digital avionics, active controltechnology, satellite-aided navigation, air traffic control, propfanairliner propulsion system development, and such advanced, lowweight/high strength materials and construction techniques asmetal matrix composites, all composite primary aircraft structures,and powder metallurgy techniques All present considerations areinformed and complicated by the fact that aviation is a highlypolitical industry, constituting an important component of nationaldefence O C

N83-25652# Federal Aviation Administration, Washington, D COffice of Aviation Policy and PlansFAA AVIATION FORECASTS. FISCAL YEARS 1983-1994Feb 1983 80 p(AD-A124611, FAA-APO-83-1) Avail NTIS HC A05/MF A01CSCL 01B

This report contains the Fiscal Years 1983-1994 FederalAviation Administration (FAA) forecasts of aviation activity at FAAfacilities These include airports with FAA control towers, air routetraffic control centers, and flight service stations Detailed .forecastswere made for the four major users of the national aviation systemair carriers, air taxi/commuters, general aviation and the militaryThe forecasts have been prepared to meet the budget and planningneeds of the constituent units of the FAA and to provide informationthat can be used by state and local authorities, by the aviationindustry and the general public The overall outlook for the forecastperiod is for moderate economic growth, relatively stable real fuelprices, and decreasing inflation Based upon these assumptions,aviation activity is forecast to increase by Fiscal Year 1994 by 97

percent at towered airports, 50 percent at air route traffic controlcenters, and 54 percent in flight services performed Hours flownby general aviation is forecast to increase 56 percent and helicopterhours flown 80 percent Scheduled domestic revenue passengermiles (RPM's) are forecast to increase 81 percent, with scheduledinternational RPM's forecast to increase by 80 percent andcommuter RPM's forecast to increase by 220 percent GRA

N83-25653# Federal Aviation Administration, Washington, D COffice of Management SystemsGENERAL AVIATION ACTIVITY AND AVIONICS SURVEYAnnual Report, 1981J C SCHWENK (Transportation Systems Center) and P WCARTER Dec 1982 110p refs(AD-A124595, FAA-MS-82-5) Avail NTIS HC A06/MF A01CSCL 01B

This report presents the results and a description of the 1981General Aviation Activity and Avionics Survey The survey wasconducted during 1982 by the FAA to obtain information on theactivity and avionics of the United States registered general aviationaircraft fleet, the dominant component of civil aviation in the U SThe survey was based on a statistically selected sample of about8 9 percent of the general aviation fleet and obtained a responserate of 61 percent Survey results are based upon response butare expanded upward to represent the total population Surveyresults revealed that during 1981 an estimated 407 million hoursof flying time were logged by the 213,226 active general aviationaircraft in the U S fleet, yielding a mean annual flight time peraircraft of 188 1 hours The active aircraft represented about 83percent of the registered general aviation fleet The report containsbreakdowns of these and other statistics by manufacturer/modelgroup, aircraft type, state and region of based aircraft, and primaryuse Also included are fuel consumption, lifetime airframe hours,avionics, and engine hours estimates In addition, tables areincluded for detailed analysis of the avionics capabilities of GAfleet GRA

N83-25654# Federal Aviation Administration, Washington, DCOffice of Aviation Policy and PlansAVIATION EXECUTIVE CONFERENCE Summary Report1981 48 p Conf held in Washington, D C , 30 June 1981(AD-A124581, FAA-APO-81-9) Avail NTIS HC A03/MF A01CSCL 01B

Partial Contents Deregulation-How Far Should the FAA Go',What Should be the FAA's Role in Encouraging and Fosteringthe Development of aviation and Helping U S AirframeManufacturers be More Competitive with Foreign Manufacturers',What User/Information Services Should Continue After CABAbolishment', Major Hub Airports Sharing Revenues with RelieverAirports, Air Traffic Control System of the Future Labor IntensiveVersus Capital Intensive, and Airport/Aircraft Noise Policy GRA

N83-25655# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of Systems and LogisticsTHE EFFECTS OF THE PRODUCTION ORIENTEDMAINTENANCE ORGANIZATION (POMO) CONCEPT ON ADTACAIRCRAFT MAINTENANCE PRODUCTIVITY AND QUALITY M.S.ThesisJ B AMEND and L E ERIKSEN Sep 1982 139 p refs(AD-A123981, AFIT-LSSR-70-82) Avail NTIS HC A07/MF A01CSCL01C

Virtually all USAF tactical fighter and interceptor units workunder the AFR 66-5 decentralized POMO concept for aircraftmaintenance This thesis used an aggregation of maintenance datafrom five ADTAC Fighter Interceptor Squadrons spanning periodspreceding and following POMO implementation Hypothesesreflecting POMO's intended effects on maintenance productivityand quality were then statistically tested using the Analysis ofVariance, Duncan's Multiple Range Test, and the Large SampleTest of Significance The final research results showed thatconversion to POMO generally improved aircraft maintenanceperformance in the ADTAC FISs, but not to any great extent

416

02 AERODYNAMICS

These findings may possibly be generalizable to other USAF tacticalair force operations Author (GRA)

N83-25656# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of Systems and LogisticsAIRFRAME RDT&E COST ESTIMATING: A JUSTIFICATION FORAND DEVELOPMENT OF UNIQUE COST ESTIMATINGRELATIONSHIPS ACCORDING TO AIRCRAFT TYPE M SThesisC L BECK, JR and D L PFEIL Sep 1982 205 p refs(AD-A123848, AFIT-LSSR-56-82) Avail NTIS HC A10/MF A01CSCL01C

Airframe RDT&E costs are invariably predicted by utilizing onegeneral cost estimating relationship (CER) regardless of aircrafttype(fighter, attack, or bomber/cargo) This practice results ininconsistent and often very significant inaccuracies in predictingweapon system development costs which may affect subsequentprogram funding This thesis examines the utility of a unique CERfor each aircraft type to be used for estimating airframedevelopment costs The methodology consisted of factor analysisand step-wise multiple regression analysis Based on the results,the authors concluded that the unique CERs are consistently andSignificantly more accurate when estimating airframe RDT&E coststhan the general CERs developed by former studies The resultsof this study should be applicable to those organizations dealingwith the procurement of aircraft airframes Author (GRA)

N83-26785*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaSOME HISTORICAL TRENDS IN THE RESEARCH ANDDEVELOPMENT OF AIRCRAFTM L SPEARMAN Apr 1983 15 p(NASA-TM-84665, NAS 1 1584665) Avail NTIS HC A02/MFA01 CSCL01B

A survey of some trends in aircraft design was made in aneffort to determine the relation between research, development,test, and evaluation (RDT and E) and aircraft mission capability,requirements, and objectives Driving forces in the history of aircraftinclude the quest for speed which involved design conceptsincorporating jet propulsion systems and low drag features Thestudy of high speed design concepts promoted new experimentaland analytical research techniques These research techniques, inturn, have lead to concepts offering new performance potentialDesign trends were directed toward increased speed, efficiency,productivity, and safety Generally speaking, the research anddevelopment effort has been evolutionary in nature and, with theexception of the transition to supersonic flight, little has occurredsince the origin of flight that has drastically changed the basicdesign fundamentals of aircraft However, this does not precludethe possibility of dramatic changes in the future since the productsof research are frequently unpredictable Advances should beexpected and sought in improved aerodynamics (reduced drag,enhanced lift, flow field exploitation), propulsion (improved enginecycles, multimode engines, alternate fuels, alternate powersources), structures (new materials, manufacturing techniques), allwith a view toward increased efficiency and utility Author

N83-26786# Advisory Group for Aerospace Research andDevelopment, Neuilly-Sur-Seme (France)AGARD BULLETIN: MEETINGS, PUBLICATIONS,MEMBERSHIPJan 1983 77 p(AGARD-BUL-83/1) Avail NTIS HC A05/MF A01

Information on all the planned meetings including dates,locations and brief descriptions of their themes is included Includedalso is a list of all publications which were issued together withtheir abstracts Complete listings of all publications which appearedsince the founding of this agency are included in the index ofpublications Information on how AGARD documents may beobtained is also given S L

N83-26787# Air Force Wright Aeronautical Labs,Wright-Patterson AFB, OhioA COLLECTION OF PAPERS IN THE AEROSPACE SCIENCESFinal Report, Dec. 1978 - Nov. 1979K S NAGARAJA, ed and J S PETTY, ed Jun 1982 660 prefs(AD-A122667, AFAPL-TR-79-2126) Avail NTIS HC A99/MFA01 CSCL 01A

A collection of thirty-five papers covering a range of topics inthe aerospace sciences, including propulsion, fluid dynamics,aerodynamics, energy conversion, and mathematical analysis ispresented The introductory paper is a biography of Dr Hans vonOham, a pioneer in the development of the aircraft jet engine

02

AERODYNAMICS

Includes aerodynamics of bodies, combinations, wings, rotors, andcontrol surfaces, and internal flow in ducts and turbomachmery

A83-33772OPTIMUM WIRE SCREENS FOR CONTROL OF TURBULENCEIN WIND TUNNELSG I DERBUNOVICH, A S ZEMSKAIA, E U REPIK, and ID PSOSEDKO (TsAGI, Uchenye Zapiski, vol 13, no 1, 1982, p11-20) Fluid Mechanics - Soviet Research (ISSN 0096-0764), vol10, Sept-Oct 1981, p 136-147 Translation refs

Recommendations are made for selecting the set of screensthat will give the most effective damping of free-stream turbulencefor a specified screen drag Attention is also given to the structureof the turbulence generated by a screen placed in nonturbulentflow Optimal geometry is sought because the introduction offlow-damping screens significantly increases the pressure drop andthe pumping penalty It is pointed out that the mechanisms of thescreen's damping effect involves primarily the reduction of thescale of the turbulence fluctuations, with the smaller fluctuationsthen being damped more rapidly than large-scale turbulence

CR

A83-33972*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaRECENT STUDIES AT NASA-LANGLEY OF VORTICAL FLOWSINTERACTING WITH NEIGHBORING SURFACESJ E LAMAR and J F CAMPBELL (NASA, Langley ResearchCenter, Hampton, VA) NATO, AGARD, Symposium on VorticalType Flows in Three Dimensions, Rotterdam, Netherlands, Apr25-28, 1983, Paper 33 p refs

The importance of leadmgedge vortical flows, which occur nearand interact with neighboring surfaces, is stressed Research inthis area conducted or sponsored by the NASA Langley ResearchCenter since 1978 is surveyed Particular attention is given to thecumulative results of a number of theoretical and experimentalstudies It is noted that these studies have been carried out inorder to understand and use this kind of flow Much of the workhas been devoted to improving the hft-to-drag ratio and pitchcharacteristics for wings in this flow, although work has also beendone on examining the unsteady and lateral characteristics C R

A83-35S35THE AERODYNAMICS OF HYPOSONIC VELOCITIES (ONFLOWS WITH LOW MACH NUMBERS) [AERODINAMIKAGIPOZVUKOVYKH SKOROSTEI /O TECHENIIAKH S MALYMICHISLAMI MAKHA/]R KH ZEITUNIAN PMTF - Zhurnal Prikladnoi Mekhaniki iTekhnicheskoi Fiziki (ISSN 0044-4626), Mar-Apr 1983, p 53-61In Russian refs

The paper introduces the concept of hyposonic flow whichdescribes slow subsonic weakly compressible gas flow Hyposonicflow is discussed with reference to the phenomena of unsteadiness,

417

02 AERODYNAMICS

viscosity, and acoustics which are connected with it Particularconsideration is given to the necessity of correctly allowing forweak compressibility in the mathematical modeling of flowphenomena The discussion is illustrated by several simpleproblems, and solutions are indicated for some of these problemsParticular attention is given to the case where S is not equal tozero and R is not equal to infinity, the case of hyposonic flowwithin a limited region, the effect of weak compressibility onviscosity, the theory of small perturbations for hyposonic flows,and the external unsteady problem B J

A83-35541CALCULATION OF SUBSONIC FLOW PAST RECTANGULARWINGS AND THEIR COMBINATIONS ON THE BASIS OF ADISCRETE VORTEX SCHEME [RASCHET OBTEKANIIAPRIAMOUGOL'NYKH KRYE'EV I IKH KOMBINATSII VDOZVUKOVOM POTOKE PO DISKRETNOI VIKHREVOISKHEME]N F VOROBEVandG N SHASHKINA PMTF - Zhurnal PnkladnoiMekhaniki i Tekhnicheskoi Fiziki (ISSN 0044-4626), Mar -Apr 1983,p 91-98 In Russian refs

The effect of the parameter K on the aerodynamiccharacteristics of rectangular-planform wings is evaluated, thevariation of K from 0 to 1 corresponds to the modeling of theintensity of a vortex sheet in the process of shedding (K = 0corresponds to nonseparated flow while K = 1 corresponds tothe limiting case of total separation) An analysis is also presentedof the effect of individual computational parameters and individualelements of a free vortex sheet on the overall aerodynamiccharacteristics Calculations of flow past combinations ofrectangular wings of small aspect ratio are presented, and resultsof calculations of normal force coefficients and pitching momentare compared with available experimental data A scheme isproposed for modeling the twisting of the vortex sheet into twovortex cores some distance from the wing B J

A83-35590PROFILE LOSSES DURING THE RELEASE OF AIR ONTO THESURFACE OF NOZZLE VANES [PROFIL'NYE POTERI PRIVYPUSKE VOZDUKHA NA POVERKHNOST' SOPLOVYKHLOPATOK]S Z KOPELEV and V V ZIKEEV Promyshlennaia Teplotekhnika(ISSN 0204-3602), vol 5, May-June 1983, p 51-59 In Russianrefs

The results of a gas-dynamic study of profile losses in nozzlevane cascades where air is released onto the surface of the vanesare presented A procedure for calculating the profile losses foran arbitrary arrangement of perforation rows is discussed wherebyallowance is made for both mixing losses and additional frictionlosses resulting from the release of the cooling agent V L

A83-35620THE SWIRL IN AN S-DUCT OF TYPICAL AIR INTAKEPROPORTIONSR W QUO and J SEDDON Aeronautical Quarterly (ISSN0001-9259), vol 34, May 1983, p 99-129 refs

Measurements were made of the static pressure, total pressure,and swirl in an S-shaped duct typical of jet air intakes Variousangles of attack and different flow-through ratios were examinedIt was determined that swirl presence in an S-duct is affected bythe interaction between pressure gradients caused by bends andby the angle of attack, the flow inertia, the viscous flow condition,and the geometry of the duct cross-sections The pattern andintensity of the swirl is dependent on the first three factors, aswell as the duct geometry A high mean total pressure at theengine face is present at a low incidence, then decreases withincreasing incidence High values of the distortion parameter athigh incidence are lowered through use of spoilers and an auxiliaryinflow area M S K

A83-35707SEPARATED FLOWS ON A CONCAVE CONICAL WING[OTRYVNYE TECHENIIA NA VOGNUTOM KONICHESKOMKRYLE]V V KRAVETS and A I SHVETS Akademna Nauk SSSR,Izvestua, Mekhanika Zhidkosti i Gaza (ISSN 0568-5281), Mar-Apr1983, p 83-91 In Russian refs

A series of models of concave conical wings were tested in awind tunnel, along with flat delta wings, at Mach 3 and angles ofattack ranging from 0 to 15 deg In comparison with flat deltawings, the concave configuration makes it possible to achievehigher shock waves, avoid additional pressure losses associatedwith transverse flows, and prevent flow over the leading edge ofthe wing at larger angles of attack Experimental data on pressuredistribution, shock waves, and separated flows are discussed indetail, and some of the results are presented in graphical form

V L

A83-35828#APPLICATIONS OF COMPUTATIONAL TECHNIQUES IN THEDESIGN OF RAMJET ENGINESM D GRIFFIN, F S BILLIG, and M E WHITE (Johns HopkinsUniversity, Laurel, MD) IN International Symposium on AirBreathing Engines, 6th, Paris, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 215-228 refs

A discussion is presented concerning computational fluiddynamics techniques for ramjet engine design and analysis whichare sufficiently efficient to allow their routine use as part of theiterative design and optimization process The applications andlimitations noted for purely mviscid analyses of inlet flowfields arecomplemented by steady state, parabolized Navier-Stokes methodsconsidering the effects of viscosity Attention is given to modelingtechniques, and to a procedure for flow field analysis, in the caseof a dual combustor ramjet O C

A83-35838#NUMERICAL COMPUTATION OF TURBULENT FLOW AROUNDTHE SPINNER OF A TURBOFAN ENGINEY OBIKANE (Ishikawajima-Harima Heavy Industries Co, Ltd,Tokyo, Japan) IN International Symposium on Air BreathingEngines, 6th, Paris, France, June 6-10, 1983, Symposium Papers

New York, American Institute of Aeronautics and Astronautics,1983, p 304-312 refs

The Reynolds stress in the flow around the spinner of a turbofanengine has been predicted with a second order turbulence modelingequation It has been shown that the large mean strain rate andthe mean shear gradient change significantly the turbulent kineticenergy and the anisotropy Especially, it is predicted that theturbulent kinetic energy is strongly intensified on the streamlinenear the spinner Therefore, one may expect that the intensifiedturbulence is swallowed into the core region of the turbofan engineThe turbulence model may be applicable for higher intensifiedturbulent flow such as the blade-to-blade flow in turbine and couldbe very useful for engine design Author

A83-35839#AERODYNAMIC OPTIMIZATION THEORY OF A 3-DAXIAL-FLOW ROTOR-BLADING VIA OPTIMAL CONTROLL GAOLIAN (Shanghai Institute of Mechanical Engineering,Shanghai, People's Republic of China) IN InternationalSymposium on Air Breathing Engines, 6th, Paris, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 313-318 refs

In this paper a theory of optimum aerodynamic design of awhole 3-D rotor-blading with cylindrical hub and casing incompressible flow is put forth It has been formulated as an optimalcontrol problem with multiple inequality constraints on control- andphase-variables, including also a constraint on centrifugal stressin rotating blades The essential feature of the present theoryconsists in its capability of handling a variety of practical designconstraints (to account for aerodynamic, cooling, material-strength,vibrational and technological requirements) in a unified manner,

418

02 AERODYNAMICS

so that the optimal solution thus obtained is surely feasible andcan be adopted for practical use Author

A83-35852#A CONTRIBUTION TO THE CALCULATION OF SECONDARYFLOWS IN AN AXIAL FLOW COMPRESSORK D PAPAILIOU (Athens, National Technical University, Athens,Greece) IN International Symposium on Air Breathing Engines,6th, Pans, France, June 6-10, 1983, Symposium Papers NewYork, American Institute of Aeronautics and Astronautics, 1983, p439-446 refs

Modifications are introduced into the theoretical developmentof flow equations based on a parabolic (boundary layer) formulationin the longitudinal flow direction and an elliptic (secondary vorticity)formulation in the transverse flow direction, introducing a simpleapproximation technique which accounts for viscous/mviscidinteraction effects in the course of viscous flow calculations Theapplication given for this approach is the case of a compressorcascade, with the theoretical modifications and the approximateviscous/mviscid interaction procedure incorporated O C

A83-35853#EXPERIMENTAL STUDY OF A HIGH-THROUGH-FLOWTRANSONIC AXIAL COMPRESSOR STAGEA J WENNERSTROM (USAF, Aero Propulsion Laboratory,Wright-Patterson AFB, OH) IN International Symposium on AirBreathing Engines, 6th, Pans, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 447-457 refs

Design features and experimental performance data are givenfor the case of a 195 kg/sec per sq m transonic axial compressorachieving a 1 95 pressure ratio at a tip speed of 457 m/sec Thisdesign incorporates several novel features that are instrumentalin the attainment of a design speed peak isentropic efficiency ofmore than 88 percent An optimum rotor tip clearance is determinedfor the design, and it is found that the placing of vortex generatorsupstream is ineffective in influencing stall margin The installing ofvortex generators on the rotor did, however, improve stall margin,and increased efficiency at speeds above 90 percent of the designspeed O C

A83-35868#EFFECT OF ENTRY BOUNDARY LAYER THICKNESS ONSECONDARY FLOWS IN AN ANNULAR CASCADE OF TURBINENOZZLE AND ROTOR BLADESM GOVARDHAN and N VENKATRAYULU (Indian Institute ofTechnology, Madras, India) IN International Symposium on AirBreathing Engines, 6th, Paris, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 585-594

This paper presents the results of some of the initialinvestigations carried out on a low speed annular cascade of turbinenozzle blades, with a view to study the secondary flows and lossesarising out of the three-dimensional nature of the flow andinteraction of such parameter like the entry boundary layers Fromthe results obtained, the spanwise variation of circumferentiallyaveraged total pressure, local loss coefficient, velocity, flow angleand pitch angle downstream of the cascade are presented Alsopresented in the paper are the contours of total pressure, velocity,flow direction and local loss coefficient at the downstream forone typical boundary layer thickness Results from linear cascadeby using rotor blades are presented in the form of total pressurecontours for two typical entry boundary thicknesses Author

A83-35873#FLOW MEASUREMENTS WITHIN ROTATING STALL CELLS INSINGLE AND MULTISTAGE AXIAL-FLOW COMPRESSORSD K DAS (New York, State University, Utica, NY) and H KJIANG (Beijing Institute of Aeronautics and Astronautics, Beijing,People's Republic of China) IN International Symposium on AirBreathing Engines, 6th, Paris, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 623-631 refs

Detailed measurements were taken with combined probescontaining fast-response transducers for the flow field and theparameter transducers for the flow field and the parameterdistributions both in single and multistage axial-flow compressorsoperating in the rotating stall regime The large amount of resultspresented in this paper reveal in detail the structure of the rotatingstall cell and show certain new features of the stalled compressorThe contents of this paper are anticipated to make a significantcontribution to the development of a physical model for rotatingstall in axial-flow compressor Author

A83-35874#FLOW IN ROTATING STALL CELLS OF A LOW SPEED AXIALFLOW COMPRESSORF A E BREUGELMANS, K MATHIOUDAKIS, and F CASALINI(Institut von Karman de Dynamique des Fluides,Rhode-Saint-Genese, Belgium) IN International Symposium onAir Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 632-642 refs

A high hub-tip ratio single stage compressor is investigatedover the entire characteristic, using fast response instrumentationThe flow field is explored in the absolute and relative referenceframe The information is digitized for further analysis of theinstantaneous and averaged flow parameters Two distinct typesof perturbations are explored the small oscillating eight cell andthe single or double cell pattern with deep stall The energy spectra,autocorrelation function and phase locked averaging technique areused in the analysis The instantaneous traces are used in thedescription of the cell structure for the deep stall case Vorticesand strong reversed flows are observed during the passage ofthe large stall cells and large radial drifts occur on the bladesurfaces Author

A83-35875#HIGH ANGLE-OF-ATTACK CASCADE MEASUREMENTS ANDANALYSISW F OBRIEN, H L MOSES, S B THOMASON, and A MYOCUM (Virginia Polytechnic Institute and State University,Blacksburg, VA) IN International Symposium on Air BreathingEngines, 6th, Pans, France, June 6-10, 1983, Symposium Papers


Results are presented from cascade tests of double-circular-arccompressor blades at high angle-of-attack A specially-designedcascade tunnel permitted operation at angles-of-attack to 28degrees with good retention of two-dimensional flow in the testsection Results from the tests are compared with predictions ofa cascade flow theory based on simultaneous solution of an inviscidfree stream and an integral boundary layer model Author

A83-36046*# Jet Propulsion Lab, California Insl of Tech,PasadenaENTRAPMENT AND MIXING IN THRUST AUGMENTINGEJECTORSL BERNAL and V SAROHIA (California Institute of Technology,Jet Propulsion Laboratory, Pasadena, CA) American Institute ofAeronautics and Astronautics, Aerospace Sciences Meeting, 21st,Reno, NV, Jan 10-13, 1983 10 p NASA-supported researchrefs(Contract N62269-80-MP-00034, AF-AFOSR-ISSA-81-00029)(AIAA PAPER 83-0172)

An experimental investigation of two-dimensional thrustaugmenting ejector flows has been conducted Measurements of

419

02 AERODYNAMICS

the shroud surface pressure distribution, mean velocity, turbulentintensities and Reynolds stresses were made in two shroudgeometries at various primary nozzle pressure ratios The effectsof shroud geometry and primary nozzle pressure ratio on the shroudsurface pressure distribution, mean flow field and turbulent fieldwere determined From these measurements the evolution of mixingwithin the shroud of the primary flow and entrained fluid wasobtained The relationship between the mean flow field, theturbulent field and the shroud surface pressure distribution isdiscussed Author

A83-36076*# Technion - Israel Inst of Tech , HaifaNUMERICAL CALCULATION OF NONLINEAR AERODYNAMICSOF WING-BODY CONFIGURATIONSE WASSERSTROM (Technion - Israel Institute of Technology,Haifa, Israel), A SEGINER (NASA, Ames Research Center, MoffettField, CA, Technion Israel Institute of Technology, Haifa, Israel),and Z RUSAK (Israel Annual Conference on Aviation andAstronautics, 24th, Tel Aviv and Haifa, Israel, February 17, 18,1982, Collection of Papers, p 187-197) AIAA Journal (ISSN0001-1452), vol 21, July 1983, p 929-936 refs


A83-36078#SINGLE- AND MULTIPLE-CRATER INDUCED NOSETIPTRANSITIONA TODISCO, B REEVES, D SIEGELMAN, and R MASCOLA(Avco Corp , Avco Systems Div , Wilmington, MA) AIAA Journal(ISSN 0001-1452), vol 21, July 1983, p 939, 940(Contract F04701-78-C-0144)


A83-36235'# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaEMPENNAGE/AFTERBODY INTEGRATION FOR SINGLE ANDTWIN-ENGINE FIGHTER AIRCRAFTB L BERRIER (NASA, Langley Research Center, TransonicAerodynamics Div, Hampton, VA) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 13p refs(AIAA PAPER 83-1126)

An extensive experimental program to determine the effects ofempennage surfaces on single and twin-engine afterbody/nozzledrag has been conducted by the Propulsion Aerodynamics Branchat the NASA Langley Research Center Empennage interferencedrag was obtained by using experimental values of afterbody/nozzledrag and computed values of empennage drag The effects of taillocation, span, number (single versus twin), toe angle, cant angle,camber and root chord length are discussed The magnitude ofempennage interference drag on single and twin engineconfigurations is examined Author

A83-36258#NUMERICAL CALCULATIONS OF TIME DEPENDENTTHREE-DIMENSIONAL VISCOUS FLOWS IN A BLADEPASSAGE WITH TIP CLEARANCEA R WADIA (General Motors Corp, Detroit Diesel Allison Div,Indianapolis, IN) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 12 p refs(AIAA PAPER 83-1171)

It is pointed out that significant grains in efficiency are possibleby minimizing the aerodynamic losses in various mechanicalcomponents of a gas turbine engine Endwall losses constitute amajor portion of the total losses, and a significant portion of thetotal endwall flow losses is attributed to tip leakage flow Wadiaand Booth (1982) have computed the two-dimensional streamlinepatterns in the tip region Several tip configurations were analyzedand the pressure side winglet was found to seal quite effectivelyThe present investigation is concerned with further improvementsin rotor-tip winglet configurations, taking into account the systematicand economical approach developed by Wadia and Booth It isfound that the pressure side winglet is a more effective sealingconfiguration than a suction side winglet The obtained numerical

results suggest that a partial shroud is the best performer amongall the members of the winglet family Attention is also given tothe development of a full three-dimensional viscous flow model ofthe tip leakage problem G R

A83-36259#PREDICTION OF STAGNATION FLOW HEAT TRANSFER ONTURBOMACHINERY AIRFOILSO K KWON, E R TURNER, and Y M KOU (General MotorsCorp, Indianapolis, IN) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 11 p refs(AIAA PAPER 83-1173)

An analytic procedure is developed for obtaining preliminarydesign predictions of nonporous turbine airfoil stagnation pointheat transfer based on the numerical solution of the compressibleboundary layer similarity equations The effective viscosity/Prandtlnumber concept is introduced to account for the effects offree-stream turbulence An existing eddy diffusivity turbulencemodel developed specifically for the analysis of cylinders incrossflow is modified to explicitly reflect the influence of arbitrarystagnation point pressure gradient Predictions for both cylinderand turbine airfoil stagnation flows are compared with results fromexisting theory and experiments Author

A83-36287*# Vigyan Research Associates, Inc, Hampton, VaMETHOD FOR CALCULATING EFFECTS OF A PROPFAN ONAIRCRAFT AERODYNAMICS AT SUBSONIC SPEEDSB CHANDRASEKARAN (Vigyan Research Associates, Inc,Hampton, VA) and G BARTLETT (George Washington University,Hampton, VA) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 15 p refs(Contract NAS1-16742)(AIAA PAPER 83-1216)

A subsonic-flow panel code has been modified to handle theeffects of a propeller wake The effects of the propeller weremodelled by a system of ring vortices of constant strengthPrinciples based on the blade element theory and the momentumtheory were used to evaluate the swirl velocity and the pressureincrease, across the propeller Theoretical calculations arecompared to experimental results at a Mach number of 0 50 Thediscrepancies between the theory and the experimental resultsare analysed Suggestions for improvements to enhance theaccuracy of the theoretical prediction are indicated Author

A83-36291*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaSTOL WIND TUNNEL TEST RESULTS FOR A TACTICALSUPERCRUISERR A HUTCHISON, M B SUSSMAN (Boeing Military AirplaneCo, Seattle, WA), R MAINQUIST (USAF, Eglin AFB, FL), and JW PAULSON, JR (NASA, Langley Research Center, Hampton,VA) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 12 p refs(Contract F33615-80-C-3001)(AIAA PAPER 83-1224)

Attention is given to the NASA Langley Research Center'stesting of a 105 percent-scale supersonic cruiser (supercruiser)aircraft model in its V/STOL wind tunnel, in order to investigatethe low speed aerodynamic characteristics of STOL enhancementdevices The STOL devices employed by the supercruiserconfiguration are high vector angle ramp nozzles, working inconjunction with a remote augmented lift system (RALS), in additionto a canard trim system Also investigated were thrustreverser/ground plane interaction effects, for the evaluation oflanding characteristics It is noted that STOL approach thrustmanagement requires the use of a partially reversing RALS nozzlewhich develops approximately 31 percent of mam nozzle thrust,and that strong nose-up interactions during ground roll, withreverser operation, may limit dry power engine thrust for brakingassistance to about 50 percent of maximum dry power O C

420

02 AERODYNAMICS

A83-36292#A HIGH SPEED WIND TUNNEL TEST EVALUATION OF STOLDEDICATED ADVANCED EXHAUST NOZZLE CONCEPTSJ G DOONAN, C J CALLAHAN (Grumman Aerospace Corp,Bethpage, NY), and D L BOWERS (USAF, Wright AeronauticalLaboratories, Wright-Patterson AFB, OH) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 198318 p refs(Contract F33615-79-C-3009)(AIAA PAPER 83-1225)

Recent studies concerned with advanced exhaust nozzleconcepts have identified numerous potential benefits for advancedtactical aircraft These benefits are related to increasedmaneuverability through vectored thrust, increased range throughreduced cruise drag, and enhanced aircraft survivability throughreduced observables The present investigation is concerned witha significant contribution to enlarging the advanced exhaust nozzledata base available for aircraft preliminary design Four advancedexhaust nozzle configurations have been studied over a Machnumber range from 0 6 to 1 45 The exhaust nozzle configurationsconsidered include an advanced, lightweight, vectoring,convergent-divergent axisymmetric nozzle, and a low aspect ratioAxisymmetric Load balanced Exhaust Nozzle Each nozzle wasexamined at representative nonafterburnmg (dry cruise) andafterburning (combat maneuver) power settings and thrust vectorangles up to 20 deg G R

A83-36324*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaA STATIC INVESTIGATION OF YAW VECTORING CONCEPTSON TWO-DIMENSIONAL CONVERGENT-DIVERGENT NOZZLESB L BERRIER and M L MASON (NASA, Langley ResearchCenter, Transonic Aerodynamics Div, Hampton, VA) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 13 p refs(AIAA PAPER 83-1288)

The flow-turning capability and nozzle internal performance ofyaw-vectoring nozzle geometries were tested in the NASA Langley16-ft Transonic wind tunnel The concept was investigated as ameans of enhancing fighter jet performance Five two-dimensionalconvergent-divergent nozzles were equipped for yaw-vectoring andexamined The configurations included a translating left sidewall,left and right sidewall flaps downstream of the nozzle throat, leftsidewall flaps or port located upstream of the nozzle throat, anda powered rudder Trials were also run with 20 deg of pitch thrustvectoring added The feasibility of providing yaw-thrust vectoringwas demonstrated, with the largest yaw vector angles beingobtained with sidewall flaps downstream of the nozzle primarythroat It was concluded that yaw vector designs that scoop orcapture internal nozzle flow provide the largest yaw-vectorcapability, but decrease the thrust the most M S K

turbulence components A blade to blade turbulence distributionwas also generated M S K

A83-36363*#PROGRESS TOWARD THE ANALYSIS OF COMPLEXPROPULSION INSTALLATION FLOW PHENOMENONP R A KERN and R G HOPCROFT (Boeing Military AirplaneCo , Seattle, WA) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 12 p refs(Contract NAS1-16150)(AIAA PAPER 83-1367)

A trend toward replacement of parametric model testing withparametric analysis for the design of aircraft is driven by the rapidlyescalating cost of wind tunnel testing, the increasing availability oflarge fast computers, and powerful numerical flow algorithms Inconnection with the complex flow phenomena characteristic ofpropulsion installations, it is now necessary to employ bothparametric analysis and testing for design procedures Powerfulflow analysis techniques are available to predict local flowphenomena However, the employment of these techniques is veryexpensive It is, therefore, necessary to link these analyses withless powerful and less expensive procedures for an accurateanalysis of propulsion installation flowfields However, theinterfacing and coupling processes needed are not available Thepresent investigation is concerned with progress made regardingthe development of suitabale linking methods Attention is givento methods of analysis for predicting the flow around a nacellecoupled to a highly swept wing G R

A83-36364#PAN AIR APPLICATIONS TO AERO-PROPULSIONINTEGRATIONA W CHEN and E N TINOCO (Boeing Commercial AirplaneCo , Seattle, WA) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 11 p refs(AIAA PAPER 83-1368)

Several diverse applications of the PAN AIR system toaeropropulsion problems are presented in order to demonstratethe versatility of the method These illustrative examples involvethe coupling of PAN AIR to a three-dimensional boundary layeranalysis for obtaining iterative solutions, and include a study ofthe internal flow losses through a calibration nozzle, the calculationof surface pressures about an isolated nacelle, the modeling ofexhaust flows, and the analysis of nacelle blowing effects on acomplete wing-body strut nacelle configuration C D

A83-36355#AERODYNAMIC MEASUREMENTS ABOUT A ROTATINGPROPELLER WITH A LASER VELOCIMETERJ LEPICOVSKY and W A BELL (Lockheed-Georgia Co , Marietta,GA) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 12 p Research supported by theLockheed-Georgia Co refs(AIAA PAPER 83-1354)

Data treatment and analysis techniques, as well as test resultswith the flowfield around propeller blades, are reported for a laservelocimetry system Triggering pulses are initiated insynchronization with the propeller speed and data is acquired ata rate down to 8 microsec between samples Data processinginvolves dividing the propeller revolution into 360 time slots with avelocity for each time slot The rms value for all correspondingtime slots for a series of propeller revolutions, when comparedwith the mean values, yields the local turbulence intensity at agiven propeller angular position Experimental data fromexamination of a two-bladed propeller are presented, includingderivation of the mean, axial, radial, and tangential velocity and

A83-36365#PANAIR PILOT CODE APPLICATION TO SUBSONIC NACELLETYPE INTERIOR FLOWSW D SIDDONS, JR (United Technologies Corp , Pratt and WhitneyGroup, East Hartford, CT) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 7 p refs(AIAA PAPER 83-1369)

This paper reports results from an investigation into theapplicability of the PANAIR Pilot Code to the calculation ofnacelle-type interior flows A flow model proposed for use in suchcalculations is found to permit the adjustment of interior flowleakage The doublet matching at network edges imposed by thePilot Code is found to be the cause of this unusual capability Aleakage parameter is defined which permits an assessment of thequality of interior flow solutions as well as providing a guide tothe calculation of low leakage solutions Pilot Code predictionsare compared to exterior and interior solutions for nacelle flowsfrom alternative calculations and to measurements of internalnacelle pressures for low speed flow at angle of attack Author

421

02 AERODYNAMICS

A83-36391*# Garrett Turbine Engine Co , Phoenix, ArizTHREE-DIMENSIONAL COMPRESSIBLE VISCOUS ANALYSISOF MIXER NOZZLESR K GOYAL, W L BLACKMORE (Garrett Turbine Engine Co,Phoenix, AZ), V HEAD, and L POVINELLI (NASA, Lewis ResearchCenter, Cleveland, OH) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 13 p refs(AIAA PAPER 83-1401)

An analysis-based design procedure for compound-mixerexhaust nozzles is presented and compared to test data Thedesign approach is based on two numerical solutions to the 3-Dviscous compressible Navier-Stokes equations an equation splittingtechnique used for the analysis of the core and bypass flow, anda parabolic marching scheme used in the analysis of the mixingduct The selection of the analytical methods through test datacomparisons and their coupling into an integrated design systemare discussed NASA test data is used to demonstrate the validityof the computations from the exhaust system rating station,upstream of the mixer lobe, to the nozzle throat An estimate ismade of the savings in development time and cost utilizing thenew procedure Author

A83-36414#FRICTION DRAG MEASUREMENTS OF ACOUSTIC SURFACEST -M LIU and J S MOUNT (Rohr Industries, Inc, Chula Vista,CA) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 10 p refs(AIAA PAPER 83-1356)

Drag measurements have been made for several acousticpanels from 25 ft/sec up to Mach 0 75, using both direct andindirect methods, at two different facilities Testing was conductedwith and without an augmented noise source It was found that,because of the mtercouplmg of the normal turbulent intensity nearthe surface and the acoustic attenuation through the face sheetand honeycomb cavity, all panels tested resulted in higher drag incomparison to a flat plate, though differently for different structuresWith the augmented noise source turned on with a spectrum typicalof that in a turbo-fan engine exhaust duct, it was found that dragwas higher than that encountered without augmented noiseEstimates of the equivalent sand-grain roughness for these surfacesat the condition tested have been made Skin-friction coefficientsmeasured have been presented as a function of Reynolds numberbased on momentum thickness Author

A83-36403#RESPONSE OF A SUPERSONIC INLET TO DOWNSTREAMPERTURBATIONST J BOGAR, M SAJBEN, and J C KROUTIL (McDonnell DouglasResearch Laboratories, St Louis, MO) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 198312 p refs(Contract N00014-80-C-0481)(AIAA PAPER 83-2017)

Experimental results are reported for flows in a ramp-type,external compression inlet with a large-aspect-ratio, rectangularcross-section, operated at a freesteam Mach number of 1 84 underthe influence of a mechanically generated downstream perturbationHigh-speed schlieren and time dependent pressure measurementswere employed extensively In supercritical operation, pressurefluctuations throughout the inlet caused by the excitation variedlinearly with the fluctuations at the exit station, even for large exitstation amplitudes In subcntical operation (buzz), the excitationinteracted nonhnearly with the naturally present, highly periodicoscillations by either modifying the natural frequency, if theexcitation was near a natural harmonic, or by having the excitationmodulate the naturally occurring oscillation In addition, theconditions at the two criticahty boundaries were determined as afunction of excitation amplitude and frequency Author

A83-36409*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaNATURAL LAMINAR FLOW DATA FROM FULL-SCALE FLIGHTAND WIND-TUNNEL EXPERIMENTSB J HOLMES, P F COY, L P YIP, P W BROWN (NASA,Langley Research Center, Hampton, VA), and C J OBARA (GeorgeWashington University, Hampton, VA) American Institute ofAeronautics and Astronautics, Annual General Aviation TechnologyFest, 8th, Wichita, KS, Nov 13, 14, 1981, Paper 22 p

Experimental results obtained at NASA Langley during studiesof natural laminar flow (NLF) over commercially produced aircraftsurfaces are reported The general aviation aircraft examined werelight aircraft, yet displayed NLF extents close to the maximumavailable and equivalent to high performance business aircraft flyingenvelopes Sublimating chemicals and acoustic detectiontechniques were employed to measure the boundary layertransition Theoretical predictions of boundary layer stability werefound to match well with the experimental data, with considerationgiven to both swept wings and the amplitudes of allowable waveson the airfoil surfaces The presence of the NLF on the airfoilsurfaces confirmed the benefits available from use of compositematerials for airfoil surfaces M S K

A83-36450THE MOTION DYNAMICS OF PARACHUTE SYSTEMS[DINAMIKA DVIZHENIIA PARASHIUTNYKH SISTEM]A I ANTONENKO, O V RYSEV, F F FATYKHOV, V MCHURKIN, and IU N IURTSEV Moscow, Izdatel'stvoMashinostroenie, 1982, 152 p In Russian refs

The present work considers the analysis of the dynamic andaerodynamic characteristics of load-parachute systems at the stageof their motion from the moment of full opening of the canopy tothe moment of landing Results are presented of linear andnonlinear analyses of the equations of motion of a load-parachutesystem corresponding to various mathematical models ageometrically invariant system, a rigid parachute with a freelysuspended load, and an inertialess parachute B J

A83-36913#A TECHNIQUE TO DETERMINE LIFT AND DRAG POLARS INFLIGHTA KNAUS (Messerschmitt-Boelkow-Blohm GmbH, Munich, WestGermany) Journal of Aircraft (ISSN 0021-8669), vol 20, July1983, p 587-593


A83-36916#WIND TUNNEL TESTS OF OVER-THE-WING NACELLESJ SZODRUCH and J KOTSCHOTE(Messerschmitt-Boelkow-Blohm GmbH, Vereinigte FlugtechmscheWerke GmbH, Bremen, West Germany) Journal of Aircraft (ISSN0021-8669), vol 20, July 1983, p 606-611 Research supportedby the Bundesministenum fuer Forschung und Technologie refs


A83-36917#IMPROVED NUMERICAL METHOD FOR UNSTEADY LIFTINGSURFACES IN INCOMPRESSIBLE FLOWA ICHIKAWA and S ANDO (Nagoya University, Nagoya, Japan)Journal of Aircraft (ISSN 0021-8669), vol 20, July 1983, p612-616 refs

An improved numerical method has been developed forunsteady thin rectangular wings in incompressible flow To satisfythe wing boundary conditions, the spanwise pressure distributionis assumed to be stepwise constant, while the chordwise integralis reduced to a finite sum using several kinds of quadratures,Cauchy and logarithmic singularities are treated appropriately Thepresent method gives excellent results over a wide range ofreduced frequency k (k = 0 0-5 0) within reasonable computertime Extension to compressible flow and to swept tapered wingsapplications is discussed briefly Author

422

02 AERODYNAMICS

A83-36920#CORRECTION TO THE WING SOURCE VELOCITY ERROR INWOODWARD'S USSAERO CODEQ J VAN DEN BROEK (National Institute for Aeronautics andSystems Technology, Pretoria, Republic of South Africa) Journalof Aircraft (ISSN 0021-8669), vol 20, July 1983, p 628-632refs

An analytical error present in the USSAERO computer codeused to compute the subsonic and supersonic potential-flowaerodynamic characteristics of aircraft configurations is described,and a correction is proposed The expressions of the USSAEROmodel for the vertical-perturbation-velocity component induced bythe linear source distribution on a wing panel (WL) is shown tobe incorrect, resulting in erroneous values of the vertical flowfieldbelow a tapered wing, regardless of the chordwise paneling schemeemployed Correct expressions for the velocity components arederived, it is shown that function G(2) in the USSAERO WLexpression must be replaced by the quantity G(2)-G(3) A furtherrefinement involves the removal of the undesirable effects of theresidual source sheet on the vertical perturbation velocities byapplying the USSAERO treatment of wing-panel linear vortexdistribution to the linear source distribution The validity of thecorrections is demonstrated for a typical case T K

A83-36922#EXPERIMENTAL INVESTIGATION OF THE EFFECTS OF WALLSUCTION AND BLOWING ON THE PERFORMANCE OF HIGHLYOFFSET DIFFUSERSW H BALL (Boeing Military Airplane Co, Seattle, WA) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 14 p(AIAA PAPER 83-1169)

Tests were conducted in the Boeing Diffuser Test Facility toinvestigate the effect on diffuser performance of centerlme offset,wall suction and blowing Effects of offset were studied using afamily of two-dimensional diffusers Effectiveness of wall suctionand blowing in controlling the diffuser boundary layer wasinvestigated initially with the highest offset two-dimensional diffuserThis was followed by a more detailed investigation of wall suctionand blowing using a three-dimensional offset diffuser modelConfiguration variables included center-line offset, hole area fordistributed suction, and blowing slot height Diffuser exit totalpressure profiles and longitudinal wall static pressure distributionswere measured to determine diffuser overall performance and toobtain an indication of local flow behavior Test results indicatethat good performance can be achieved for diffusers with largeoffset by using small amounts of wall suction or blowing upstreamof the separation point Author

A83-36924#DEFINITION OF VECTORED NONAXISYMMETRIC NOZZLEPLUMESM COMPTON and D L BOWERS (USAF, Wright AeronauticalLaboratories, Wright-Patterson AFB, OH) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 198314 p refs(AIAA PAPER 83-1290)

In approximately 1971, the nonaxisymmetnc exhaust nozzleemerged as a large contributor to tactical aircraft missionperformance These nozzles, especially if equipped with thefunctions of thrust vectoring and thrust reversing, can increaseaircraft maneuverability, agility, provide STOL capability, andincrease aircraft survivability Many advanced aircraft concepts arebeing configured with this nozzle type In connection with theimportance of this technology, it was determined that a need existedfor a comprehensive investigation of nonvectored and vectorednonaxisymmetnc exhaust plumes issuing from highly integratednozzles in a general advanced aircraft configuration Anexperimental investigation was initiated with the objective to define,with a very fine survey grid, the characteristics of an integratednonaxisymmetnc exhaust nozzle plume to establish an empiricaldata base and to update analytical aircraft performance prediction

techniques A description is provided of the approach taken andthe apparatus utilized in the study G R

N83-25657*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioEXPERIMENTAL RESULTS OF A DEFLECTED THRUST V/STOLNOZZLE RESEARCH PROGRAMP L BURSTADT and A L JOHNS Mar 1983 26 p refsPresented at the 21st Aerospace Sci Conf, Reno, Nev, 10-13Jan 1983, sponsored by AIAA Original contains colorillustrations(NASA-TM-83969, E-1539, MAS 1 1583069) Avail NTIS HCA03/MF A01 ' CSCL 01A

Four deflected thrust nozzle concepts, designed to operate atthe low pressure ratio typical of high bypass-ratio turbofan enginesfor medium speed (subsonic) V/STOL aircraft, were studied Mapsof overall performance characteristics and exit velocity distributionsare used to highlight similarities and differences between the fourconcepts Analytically determined secondary flows at the exit of a90 deg circular pipe bend are compared with the experimentalresults from the more complex three dimensional geometries Therelative impact of total-pressure losses and secondary flows onnozzle thrust coefficient is addressed by numerical integration ofexit velocity measurements Author

N83-25658*# Georgia Inst of Tech , Atlanta School ofAerospace EngineeringHELICOPTER ROTOR LOADS USING DISCRETIZED MATCHEDASYMPTOTIC EXPANSIONS Final ReportG A PIERCE and A R VAIDYANATHAN May 1983 76 prefs(Contract NAS1-16817)(NASA-CR-166092, NAS 1 26166092) Avail NTIS HC A05/MFA01 CSCL 01A

The numerical practicality of a matched asymptotic expansionapproach for the computation of unsteady three dimensionalairloads on a helicopter rotor was improved This effort utilizes adiscretized repesentation of the doublet strength distribution andhelical streamlines to decrease the computational requirements ofthe original analysis The continuous variation of the doubletstrength was approximated by piecewise constant or piecewisequadratic distributions, and the helical trajectory of a fluid particlewas approximated by connected straight line segments As a directresult of these simplified representations the computational timerequired for the execution of a typical flight condition was reducedby an order of magnitude with respect to the requirements of theoriginal analysis Airloads which were computed using thediscretized method for a two bladed model rotor and a full scalefour bladed rotor are in close agreement with measured resultsand airloads from the original asymptotic analysis For conditionscharacterized by significant rotor/wake interaction the piecewiseconstant representation requires a reduced azimuth spacing tomaintain acceptable accuracy S L

N83-25659*# Georgia Inst of Tech, Atlanta School ofAerospace EngineeringHELICOPTER ROTOR LOADS USING MATCHED ASYMPTOTICEXPANSIONS: USER'S MANUAL Final ReportG A PIERCE and A R VAIDYANATHAN May 1983 92 p(Contract NAS1-16817)(NASA-CR-166093, NAS 1 26166093) Avail NTIS HC A05/MFA01 CSCL 01A

Computer programs were developed to implement thecomputational scheme arising from Van Holten's asymptoticmethod for calculating airloads on a helicopter rotor blade in forwardflight, and a similar technique which is based on a discretizedversion of the method The basic outlines of the two programsare presented, followed by separate descriptions of the inputrequirements and output format Two examples illustrating job entrywith appropriate input data and corresponding output are includedAppendices contain a sample table of lift coefficient data for theNACA 0012 air foil and listings of the two programs S L

423

02 AERODYNAMICS

N83-25660*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaHIGH REYNOLDS NUMBER TESTS OF THE CAST 10-2/DOA 2AIRFOIL IN THE LANGLEY 03-METER TRANSONICCRYOGENIC TUNNEL, PHASE 1D A DRESS (Kentron International, Inc), P D MCGUIRE, ESTANEWSKY (DFVLR, West Germany), and E J RAY May1983 347 p refs(NASA-TM-84620, MAS 1 1584620) Avail NTIS HC A15/MFA01 CSCL01A

A wind tunnel investigation of an advanced technology airfoil,the CAST 10-2/DOA 2, was conducted in the Langley 03 meterTransonic Cryogenic Tunnel ( 0 3 m TCT) This was the first of aseries of tests conducted in a cooperative National Aeronauticsand Space Administration (NASA) and the Deutsche Forschungs-und Versuchsanstalt fur Luft- und Raumfahrt e V (DFVLR) airfoilresearch program Test temperature was varied from 280 K to100 K to pressures from slightly above 1 to 5 8 atmospheresMach number was varied from 0 60 to 0 80, and the Reynoldsnumber (based on airfoil chord) was varied from 4 x 10 to the 8thpower to 45 x 10 to the 6th power This report presents theexperimental aerodynamic data obtained for the airfoil and includesdescriptions of the airfoil model, the 03 m TCT, the testinstrumentation, and the testing procedures Author

N83-25662*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioNASA LOW-SPEED CENTRIFUGAL COMPRESSOR FORFUNDAMENTAL RESEARCHJ R WOOD, P W ADAM, and A E BUGGELE 1983 13 prefs Presented at the 19th Joint Propulsion Conf and TechDisplay, Seattle, 27-29 Jun 1983, sponsored by AIAA, SAE andASME(NASA-TM-83398, E-1675, NAS 1 1583398) Avail NTIS HCA02/MF A01 CSCL 01A

A centrifugal compressor facility being built by the NASA LewisResearch Center is described, its purpose is to obtain benchmarkexperimental data for internal flow code verification and modelingThe facility will be heavily instrumented with standard pressureand temperature probes and have provisions for flow visualizationand laser Doppler velocimetry The facility will accommodaterotational speeds to 2400 rpm and will be rated at pressures to1 25 atm The initial compressor stage for testing is geometricallyand dynamically representative of modern high-performance stageswith the exception of Mach number levels Design exit tip speedfor the initial stage is 500 ft/sec with a pressure ratio of 1 17The rotor exit backsweep is 55 deg from radial M G

N83-25665*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifPRESSURES MEASURED IN FLIGHT ON THE AFT FUSELAGEAND EXTERNAL NOZZLE OF A TWIN-JET FIGHTERJ NUGENT, T J PLANT, R A DAVIS, and N V TAILLON May1983 90 p refs(NASA-TP-2017, H-1161, NAS 1 602017) Avail NTIS HCA05/MF A01 CSCL 01A

Fuselage, boundary layer, and nozzle pressures were measuredin flight for a twin jet fighter over a Mach number range from 0 60to 200 at test altitudes of 6100, 10,700, and 13,700 meters forangles of attack ranging from 0 deg to 7 deg Test data wereanalyzed to find the effects of the propulsion system geometryThe flight variables, and flow interference The aft fuselage flowfield was complex and showed the influence of the vertical tail,nacelle contour, and the wing Changes in the boattail angle ofeither engine affected upper fuselage and lower fuselage pressurecoefficients upstream of the nozzle Boundary layer profiles at theforward and aft locations on the upper nacelles were relativelyinsensitive to Mach number and altitude Boundary layer thicknessdecreased at both stations as angle of attack increased above 4deg Nozzle pressure coefficient was influened by the vertical tail,horizontal tail boom, and nozzle interfacing, the last two tendedto separate flow over the top of the nozzle from flow over thebottom of the nozzle The left nozzle axial force coefficient was

most affected by Mach number and left nozzle boattail angle AtMach 0 90, the nozzle axial force coefficient was 0 0013 Author

N83-25666*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaEFFECT OF EMPENNAGE LOCATION ON TWIN-ENGINEAFTERBODY-NOZZLE AERODYNAMIC CHARACTERISTICS ATMACH NUMBERS FROM 0.6 TO 1.2L D LEAVITT May 1983 223 p refs(NASA-TP-2116, L-15527, NAS 1 602116) Avail NTIS HCA10/MFA01 CSCL01A

The Langley 16-foot transonic tunnel was used to determinethe effects of several empennage and afterbody parameters onthe aft-end aerodynamic characteristics of a twin-engine fighter-typeconfiguration Model vanables were as follows horizontal tail axiallocation and incidence, vertical tail axial location and configuration(twin- versus single-tail arrangements), tail booms, and nozzlepower setting Tests were conducted over a Mach number rangefrom 0 6 to 1 2 and over an angle-of-attack from -2 deg to 10deg Jet total-pressure ratio was varied from jet off to approximately100 Author

N83-25667*# Kansas Univ Center for Research, Inc , LawrenceFlight Research LabANALYSIS OF NONPLANAR WING-TIP-MOUNTED LIFTINGSURFACES ON LOW-SPEED AIRPLANES Final ReportC P VANDAM and J ROSKAM Washington NASA Jun1983 175 p refs(Contract NSG-1633)(NASA-CR-3684, NAS 1 263684, KU-FRL-427-1) Avail NTISHCA08/MFA01 CSCL 01A

Nonplanar wing tip mounted lifting surfaces reduce lift induceddrag substantially Wmglets, which are small, nearly vertical,wmglike surfaces, are an example of these devices To achievereduction in lift induced drag, winglets produce significant sideforces Consequently, these surfaces can seriously affect airplanelateral directional aerodynamic characteristics Therefore, theeffects of nonplanar wing tip mounted surfaces on the lateraldirectional stability and control of low speed general aviationairplanes were studied The study consists of a theoretical and anexperimental, in flight investigation The experimental investigationinvolves flight tests of winglets on an agricultural airplane Resultsof these tests demonstrate the significant influence of winglets onairplane lateral directional aerodynamic characteristics It is shownthat good correlations exist between experimental data andtheoretically predicted results In addition, a lifting surface methodwas used to perform a parametric study of the effects of variouswinglet parameters on lateral directional stability derivatives ofgeneral aviation type wings S L

N83-25668# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringWIND TUNNEL INVESTIGATION OF VARYING HINGED FLAPSM.S. ThesisH J PRICE, JR Dec 1982 110p refs(AD-A124703, AFIT/GAE/AA/82D-23) Avail NTIS HC A06/MFA01 CSCL 14B

The objective of this thesis was to compare thin-airfoiltheoretical predictions of the change in zero-lift angle of attackdivided by flap deflection versus flap-hinge location and the changein moment coefficient about the aerodynamic center GRA

N83-25669# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringTRANSIENT HEAT-TRANSFER MEASUREMENT TECHNIQUE INWIND TUNNEL AND DATA ANALYSIS TECHNIQUE USINGSYSTEM IDENTIFICATION THEORY M.S. ThesisY K WOO Dec 1982 93 p refs(AD-A124663, AFIT/GAE/AA/82D-34) Avail NTIS HC A05/MFA01 CSCL 14B

A transient maneuver testing technique has been developedby the Air Force Flight Test Center (AFFTC) for aerothermodynamicevaluation of the Space Shuttle Orbiter Thermal Protection System

424

02 AERODYNAMICS

(IPS) during reentry The objectives are to determine the feasibilityof the testing technique and the feasibility of using the transientmaneuver technique for wind tunnel heat transfer measurementsThe transient maneuver technique can enhance the capability ofwind tunnel testing by reducing the overall required testing time,and in turn lower the cost of testing significantly Wind tunneldata were obtained using the TPS materials of the Orbiter aswind tunnel test articles The principle finding indicates the heatingestimates are significantly lower for the TPS test articles than thethin skin test article and Eckert theory The discrepancy is believedto be caused mainly by the non-isothermal wall effect Finally, thetransient maneuver testing technique has been proven since thetransient maneuvers agree well with the steady state results

GRA

N83-25670# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringTHEORETICAL DETERMINATION OF THE LIFT OF ASIMULATED EJECTOR WING M S ThesisJ T DOMALSKI Dec 1982 74 p refs(AD-A124695, AFIT/GAE/82D-10) Avail NTIS HC A04/MFA01 CSCL 12A

The solution procedure and supporting theory have beendeveloped for calculation of the lift per unit span of an ejectorwing model Model consists of two vortex sheets A point sinkand a point source in a uniform stream The solution is shown tobe dependent on the number of control points used and examplesusing five control points are presented A FORTRAN computerprogram for the Five-Control-Point case is presented

Author (GRA)

N83-25671# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringWIND TUNNEL TEST OF A C-18 AIRCRAFT MODIFIED WITHTHE ADVANCED RANGE INSTRUMENTATION AIRCRAFTRADOME M.S. ThesisD M SPRINKEL Dec 1982 185 p refs(AD-A124771, AFIT/GAE/AA/82D-28) Avail NTIS HC A09/MFA01 CSCL 20D

The Air Force intends to modify Boeing 707-320C aircraft (AirForce designation, C-18) with the large blunt nosed AdvancedRange Instrumentation Aircraft (ARIA) radome formerly installedon EC-135 aircraft This modification will significantly increasefuselage area forward of the aircraft center of gravity and isexpected to reduce longitudinal and directional stability, andincrease drag These anticipated aerodynamic changes wereevaluated from data gathered on a modified (ARIA) gathered ona modified (ARIA) and unmodified (BASIC) 1/100 scale modelC-18 tested in the AFIT five foot low speed wind tunnel GRA

N83-25673# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringA WIND TUNNEL STUDY OF THE EFFECTS OF ACLOSE-COUPLED CANARD ON THE AERODYNAMICCHARACTERISTICS OF A FORWARD-SWEPT WING ININCOMPRESSIBLE FLOW M.S. ThesisP M WEAVER Dec 1982 237 p refs(AD-A124722, AFIT/GAE/AA/82D-30) Avail NTIS HC A11/MFA01 CSCL 01C

Low speed wind tunnel tests and a boundary layer flowvisualization study were conducted in the Air Force Institute ofTechnology fourteen inch wind tunnel to determine the differencesin the aerodynamic characteristics among a forward-swept wingand several forward-swept wing/canard configurations Both thewing and canard were constructed with an NACA 0006 airfoilsection and had quarter chord sweeps of -30 and +40 deg,respectively All tests were conducted at a dynamic pressure of25 6 Ibf/sg ft and a Reynolds number of 1 9 x 100,000 based onthe wing mean aerodynamic chord The results show that thechanges in the aerodynamic characteristics are dependent uponcanard location relative to the wing, canard incidence, and modelangle of attack The largest increases in CL were observed forthe two canard positions above and closest to the wing A decrease

in CM was noted as the canard location changed vertically fromthe upper to the lower test positions An increase in CD occurredas the canard location approached the wing horizontallyComparison of the force and moment data with the flow studyphotographs suggests that the canard wake/vortex system isresponsible for the changes in the wing/canard aerodynamiccharacteristics GRA

N83-25674# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringAPPLICATION OF A FINITE DIFFERENCE METHOD TO THETRANSONIC AIRFOIL PROBLEM M.S. ThesisM P BURKE Dec 1982 52 p refs(AD-A124720, AFIT/GAE/AA/79D-4) Avail NTIS HC A04/MFA01 CSCL 20D

This study presents the development and evaluation of anumerical solution technique used to analyze the two dimensionaltransonic airfoil problem The full potential equation of motion andthe irrotationality condition are used for the governing equationsA coordinate transformation is applied to the governing equationsto limit the domain of the problem and for easier application ofthe boundary conditions The method of lines is then used toreduce the equations from partial to ordinary differential equationsSolutions obtained using this numerical solution technique arecompared to published data for both incompressible andcompressible flowfield cases It is concluded that the solutiontechnique developed in this study is accurate and efficient whenanalyzing subcritical flowfields around circular airfoil shapes

Author (GRA)

N83-25675# Naval Ship Research and Development Center,Bethesda, Md Aviation and Surface Effects DeptWIND TUNNEL INVESTIGATION OF CARGO EXTRACTIONPARACHUTES IN THE WAKE OF A LOCKHEED C-141BSTARLIFTER AIRCRAFT Final Report, Jul. - Sep. 1981G G HUSON Aug 1982 86 p refs(Contract MIPR-79-102, MIPR-79-404)(AD-A124523, DTNSRDC/ASED-82/09) Avail NTIS HCA05/MF A01 CSCL 01C

Wind tunnel investigations were conducted to probe the wakeof a C-141 aircraft in an airdrop configuration A rake with twelve5-hole yaw head probes measured velocities at various positionsin the wake, and these measurements were used to compute thevorticity of the wake In addition, motion pictures and forcemeasurements were taken with three differently sized extractionparachute models attached to the model aircraft by three extractionlines of different lengths Correlation of parachute behavior withthe airflow data indicates that the vortex shed by the inboardflaps and the fuselage-wing junction causes an instability in theperformance of the smallest parachute models while theperformance of the larger parachute models is relativelyunaffected Author (GRA)

N83-25676# General Dynamics Corp, Fort Worth, TexFORCE AND PRESSURE MEASUREMENTS ON A RESEARCHMODEL WITH A LOW-, MID- AND T-TAIL AT MACH NUMBERSOF 0.60 TO 0.90. VOLUME 2: TABULATED DATA Final Report,15 Apr. - 14 Dec. 1982R A COX Dec 1982 850 p 2 Vol(Contract N00014-82-C-0340, RF41411801)(AD-A124068, FZA-540-VOL-2) Avail NTIS HC A99/MF A01CSCL 01C

An investigation of the effects of a low-, mid, and T-Tail onconfiguration aerodynamics was carried out in the NASA/AmesResearch Center 14-Foot Transonic Wind Tunnel A baseline wingand a wing refined with the use of numerical optimization weretested alone and in conjunction with a horizontal tail in a low-,mid-, and T-Tail arrangement Wing and horizontal tail pressuredata and force data were obtained in the Mach number range060 to 090 and at angles of attack from -6 to +28 deg Theall-flying horizontal tail was tested at angles of -10, 0, and +10deg This report presents the complete set of longitudinal

425

02 AERODYNAMICS

aerodynamic data and static pressure data Volume I presents ananalysis and summary of these data Author (GRA)

N83-25677# Royal Aircraft Establishment, Farnborough(England)FINITE DIFFERECNCE CALCULTION OF AN INVISCIDTRANSONIC FLOW OVER OSCILLATING AIRFOILST ISHIGURO Oct 1980 45 p refs Transl into ENGLISHfrom Japan Natl Aerospace Lab (Japan), no TR-632, Oct 1980(AD-A123982, RAE-LIBRARY-TRANS-2087, DRIC-BR-86199)Avail NTIS HC A03/MF A01 CSCL 20D

A procedure is presented to calclate the compressible inviscidpitch In order to treat precisely boundary conditions on theoscillating airfoil surface and at infinity, the exterior of the airfoilshaped contour in the physical plane is mapped onto a rectanglein a computational plane The two dimensonal unsteady Eulerequations are solved there by the Lax-Wendroff finite differencescheme with artificial viscosity Test calculations were made forthe unsteady flows over the Joukowski airfoil and the NACA 0012airfoil oscillating in pitch, in order to obtain several individual flowpatterns The resulting unsteady pressure distributions, shock wavelocations, etc, are presented Furthermore, the unsteady numericalresults obtained by this procedure for the NLP 7301 airfoil andthe NACA 64A010 airfoil are compared with the experimentalones GRA

N83-25679# McDonnell-Douglas Research Labs , St Louis, MoFlight Sciences DeptHIGHER-ORDER COMPUTATIONAL METHODS FORTRANSONIC WING/BODY FLOWFIELDS Final Report, 16 Mar.1981-30 Sep. 1982L T CHEN 30 Sep 1982 54 p refs(Contract N00167-81-C-0057)(AD-A124079, DTNSRDC/ASED-CR-03-82, MDC-Q0773) AvailNTIS HC A04/MF A01 CSCL 01C

This report presents the development of high-orderfinite-difference schemes for application to transonic wing-bodyflow calculations These schemes treat supersonic flows andshocks more accurately than most existing schemes A transformedfull potential equation in a general curvilinear coordinate systemis derived, and higher-order operators are introduced A newshock-point operator produces Mach number jumps at a shockthat agree reasonably well with Rankme-Hugoniot values Second-,and third-order, quasi-conservative, and fully conservative schemesare thereby developed for general geometries where flow directionscan be approximately aligned with coordinate lines in supersonicregions The fully conservative schemes are developed bymodifying an existing finite-volume algorithm, while thequasi-conservative schemes are developed by solving thetransformed full potential equation directly with the addition of thesecond- and third-order artificial viscosities at supersonic points,and the corresponding first- and second-order shock-pointoperators at shock points Author (GRA)

N83-25682# Advisory Group for Aerospace Research andDevelopment, Neuilly-Sur-Seme (France)TECHNICAL EVALUATION REPORT ON THE FLUID DYNAMICSPANEL SPECIALISTS' MEETING ON PREDICTION OFAERODYNAMIC LOADS ON ROTORCRAFTH R VELKOFF (Ohio State Umv , Columbus) Feb 1983 14 prefs Meeting held in London, 17-18 May 1982(AGARD-AR-189, ISBN-92-835-1445-9) Avail NTIS HCA02/MF A01

While a broad overview of work being done on (1) rotor bladeaerodynamic characteristics, (2) wakes and aerodynamic effectsof rotorcraft and wind turbines, and (3) rotor airloads predictionsprograms was presented, a serious concern remains that the intentof the conferenceas was not fully met Few papers evidencedexperimental correlations of the aerodynamic forcing functions thatwere at a level similar to the extensive models and codesdiscussed Most of the data used for evaluations were structuralresponse data or were dependent on that response Codes andanalysis were not adequately verified Adequate data bases for

verification are not generally available and usually lack importantsuch as flow velocities, pressures, or other measurements takensimultaneously Experimental efforts were often run independentlyof the analytical programs and often do not meet the needs ofthe programs A R H

N83-26815*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaSOME RECENT APPLICATIONS OF XTRAN3SD A SEIDEL, R M BENNETT, and R H RICKETTS May 198312 p refs Proposed for presentation at the AIAA Appl AerodynConf, Danvers, Mass , 13-15 Jul 1983(NASA-TM-85641, NAS 1 1585641) Avail NTIS HC A02/MFA01 CSCL 01A

A time marching finite difference code, XTRAN3S that solvesthe three dimensional transonic small perturbation equation forflow over isolated wings was developed During initial applicationsof the program, problems were encountered in the prediction ofunsteady forces The use of a revised grid and force calculationscheme improved those predictions Comparisons are madebetween predicted and experimental pressure data for a rectangularsupercritical wing Comparisons of steady and unsteady data at Msub infinity = 0 700 show good agreement between calculatedand experimental values A comparison of steady data at M subinfinity 0 825 shows poor agreement between calculations andexperiment Program difficulties were encountered with swept andtapered configurations S L

N83-26816*# Pratt and Whitney Aircraft Group, East Hartford,Conn Commercial EngineeringMODEL AERODYNAMIC TEST RESULTS FOR A REFINEDACTUATED INLET EJECTOR NOZZLE AT SIMULATEDTAKEOFF AND CRUISE CONDITIONS Final ReportD P NELSON Jun 1983 80 p refs(Contract NAS3-22738)(NASA-CR-168051, NAS 1 26 168051, PWA-5768-29) AvailNTIS HC A05/MF A01 CSCL 01A

Wind tunnel model tests were conducted to demonstrate theaerodynamic performance improvements of a refined actuated inletejector nozzle Models of approximately one-tenth scale wereconfigured to simulate nozzle operation at takeoff, subsonic cruise,transonic cruise and supersonic cruise Variations of modelcomponents provided a performance evaluation of ejector inletand exit area, forebody boattail angle and ejector inlet operationin the open and closed mode Approximately 700 data pointswere acquired at Mach numbers of 0, 0 36, 0 9, 1 2, and 2 0 for awide range of nozzle flow conditions Results show that relativeto two ejeclor nozzles previously tested performance was improvedsignificantly at takeoff and subsonic cruise performance, a C subf of 0 982, was atttamed equal to the high performance of theprevious tests The established advanced supersonic transportpropulsion study performance goals were met or closelyapproached at takeoff and supersonic cruise Author

N83-26818*# McDonnell-Douglas Corp, St Louis, MoAIRCRAFT AERODYNAMIC PREDICTION METHOD FORV/STOL TRANSITION INCLUDING FLOW SEPARATIONB R GILMER, G A MINER, and D R BRISTOW Moffett Field,Calif NASA Ames Research Center Apr 1983 93 p refs(Contract NAS2-11161)(NASA-CR-166467, NAS 1 26 166467) Avail NTIS HC A05/MFA01 CSCL 01A

A numerical procedure was developed for the aerodynamicforce and moment analysis of V/STOL aircraft operating in thetransition regime between hover and conventional forward flightThe trajectories, cross sectional area variations, and massentramment rates of the jets are calculated by the Adler-BaronJet-m-Crossflow Program The inviscid effects of the interactionbetween the jets and airframe on the aerodynamic properties aredetermined by use of the MCAIR 3-D Subsonic properties aredetermined by use of the MCAIR 3-D Subsonic Potential FlowProgram, a surface panel method In addition, the MCAIR 3-DGeometry influence Coefficient Program is used to calculate a

426

02 AERODYNAMICS

matrix of partial derivatives that represent the rate of change ofthe inviscid aerodynamic properties with respect to arbitrarychanges in the effective wing shape Author

N83-26819*# Pennsylvania State Univ , University ParkEND WALL FLOW CHARACTERISTICS AND OVERALLPERFORMANCE OF AN AXIAL FLOW COMPRESSOR STAGEFinal ReportN SITARAM and B LAKSHMINARAYANA Washington NASAFeb 1983 141 p refs(Contract NSG-3032)(NASA-CR-3671, MAS 1 263671, PSU/TURBO-82-5) AvailNTIS HC A07/MF A01 CSCL 01A

This review indicates the possible future directions for researchon endwall flows in axial flow compressors Theoreticalinvestigations on the rotor blade endwall flows in axial flowcompressors reported here include the secondary flow calculationand the development of the momentum integral equations for theprediction of the annulus wall boundary layer The equations forsecondary vorticity at the rotor exit are solved analytically Thesolution includes the effects of rotation and the viscosity Themomentum integral equations derived include the effect of theblade boundary layers The axial flow compressor facility of theDepartment of Aerospace Engineering at The Pennsylvania StateUniversity, which is used for the experimental investigations ofthe endwall flows, is described in some detail The overallperformance and other preliminary experimental results arepresented Extensive radial flow surveys are carried out at thedesign and various off design conditions These are presentedand interpreted in this report The following experimentalinvestigations of the blade endwall flows are carried out (1) Rotorblade endwall flows The following measurements are carried outat four flow coefficients (a) The rotor blade static pressures atvarious axial and radial stations (with special emphasis near theblade tips) (b) The hub wall static pressures inside the rotor bladepassage at various axial and tangential stations (2) IGV endwallflows The following measurements are carried out at the designflow coefficient (a) The boundary layer profiles at various axialand tangential stations inside the blade passage and at the bladeexit (b) Casing static pressures and limiting streamline anglesinside the blade passage B W

N83-26820*# United Technologies Corp , Stratford, ConnEXPERIMENTAL STUDY OF MAIN ROTOR/TAILROTOR/AIRFRAME INTERACTIONS IN HOVER. VOLUME 1:TEXT AND FIGURESD T BALCH, A SACCULLO, and T W-SHEENY Jun 1983491 p refs(Contract NAS2-10770)(NASA-CR-166485, MAS 1 26 166485, SER-510112-VOL-1)Avail NTIS HC A21/MFA01 CSCL 01A

To assist in identifying and quantifying the relevant parametersassociated wrth the complex topic of main rotor/fuselage/tail rotorinterference, a model scale hover test was conducted in the ModelRotor Hover Facility The test was conducted using the basicmodel test rig, fuselage skins to represent a UH-60A BLACK HAWKhelicopter, 4 sets of rotor blades of varying geometry (i e, twist,airfoils and solidity) and a model tail rotor that could be relocatedto give changes in rotor clearance (axially, laterally, and vertically),can't angle and operating model (pusher or tractor) The descriptionof the models and the tests, data analysis and summary (includingplots) are included The customary system of units gas used forprincipal measurements and calculations Expressions in both SIunits and customary units are used with the SI units stated firstand the customary units afterwords, in parenthesis S L

N83-26821*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaEFFECTS OF VARYING PODDED NACELLE-NOZZLEINSTALLATIONS ON TRANSONIC AEROPROPULSIVECHARACTERISTICS OF A SUPERSONIC FIGHTER AIRCRAFTF J CAPONE and D E REUBUSH May 1983 337 p refs(NASA-TP-2120, L-15525, NAS 1 602120) Avail NTIS HCA15/MF A01 CSCL 01A

The aeropropulsive characteristics of an advanced twin enginefighter designed for supersonic cruise was investigated in the 16foot Transonic Tunnel The performance characteristics ofadvanced nonaxisymmetnc nozzles installed in various nacellelocations, the effects of thrust induced forces on overall aircraftaerodynamics, the trim characteristics, and the thrust reverserperformance were evaluated The major model variables includednozzle power setting, nozzle duct aspect ratio, forward, mid, andaft nacelle axial locations, inboard and outboard underwmg nacellelocations, and underwmg and overwing nacelle locations Thrustvectoring exhaust nozzle configurations included a wedge nozzle,a two dimensional convergent divergent nozzle, and a singleexpansion ramp nozzle, each with deflection angles up to 30 degIn addition to the nonaxisymmetnc nozzles, an axisymmetnc nozzleinstallation was also tested The use of a canard for trim wasalso assessed S L

N83-26822*# Lockheed-Georgia Co , MariettaEXPERIMENTAL STUDIES OF THE SEPARATING CONFLUENTBOUNDARY-LAYER. VOLUME 1: SUMMARY Final ReportJ A BRADEN, R R WHIPKEY, G S JONES, and D E LILLEYNASA Washington Jun 1983 165 p refs(Contract NAS1-16028)(NASA-CR-3655, NAS 1 263655, LG-82-ER-0184) Avail NTISHC A08/MF A01 CSCL 01A

Test descriptions and results are documented from anexperimental, low speed study of the separating confluent boundarylayer on a NASA GAW-1 (General Aviation) high lift airfoil Theairfoil was tested in a variety of high lift configurations comprisedof leading edge slat and trailing edge flap combinations The primarytest instrumentation was a two dimensional, laser velocimeter (LV)system operating in a backscatter mode Surface pressures andcorresponding LV-denved, boundary layer profiles are given in termsof velocity components, turbulence intensities and Reynolds shearstresses as characterizing confluent boundary layer behavior upto and beyond stall Comparisons are given between LV-denvedprofiles and associated boundary layer parameters and thoseobtained from more conventional instrumentation such as pitotstatic traverses, Preston tube measurements and hot wire surveysA descriptive summary of the experimental set up along with limitedtest results are presented Pertinent comparisons of the resultsare made where possible with those from other sources Author

N83-26824# Aeronautical Research Labs, Melbourne(Australia)PROGRAMS FOR THE TRANSONIC WIND TUNNEL DATAPROCESSING INSTALLATION. PART 10: SIX COMPONENTMEASUREMENTS UPDATEDJ B WILLIS 1982 33 p refs(AD-A122248, ARL-AERO-TECH-MEMO-341 -PT-10,AR-002-900-PT-10) Avail NTIS HC A03/MF A01 CSCL 09B

The current version of the program used for 6 componentmeasurements using strain gauge balances and the PDP8/Iinstallation in the Transonic Wind Tunnel is described Changesto the original program include on-line display, model weightcorrection, and operation with the Pollock strain gaugeequipment A R H

427

02 AERODYNAMICS

N83-26825# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringCOMPUTATION OF INCOMPRESSIBLE POTENTIAL FLOWOVER AN AIRFOIL USING A HIGH ORDER AERODYNAMICPANEL METHOD BASED ON CIRCULAR ARC PANELS Ph.D.ThesisJ DEJONG Aug 1982 269 p refs(AD-A124896, AFIT/DS/AA/82-1) Avail NTIS HC A12/MF A01CSCL 12A

A new two dimensional panel method has been developedThis method uses a new approximating element, the circular arc,and a new singularity representation, the sine series, and allintegrations are performed analytically for maximum computationalefficiency The method was applied to a circular cylinder and toseveral different types of airfoils, and a number of characteristicswhich define the method were varied to determine their effectson the solution Major conclusions from this study were that themethod produced very accurate solutions over the major part ofthe airfoil, error reduction occurred as both the number of panelsand the number of terms in the series were increased, the effectof point source location was large but was local and could becontrolled, the method was generally insensitive to minor variationsin panelling, and the accuracy of the solution increased as panelcurvature was increased from relatively flat to circular GRA

03

AIR TRANSPORTATION AND SAFETY

Includes passenger and cargo air transport operations, and aircraftaccidents

A83-33545#ADVANCED NAVIGATION SYSTEMS AND FUELCONSERVATIONC H SIMPSON (Air Canada, Montreal, Canada) CanadianAeronautics and Space Journal (ISSN 0008-2821), vol 29, March1983, p 14-16

Attention is confined to the savings that can be realized fromimprovements in operating procedures and navigation procedures,including advanced navigation systems The Flight ManagementSystem is linked to the avionic flight control system on theL-1011-500 Tristar The computer receives information from theengines, the central air data system, and the navigation receiversIt processes the information in accordance with a predeterminedprogram and sends control signals to the autopilot and auto-throttlesystem The way in which the Inertial Navigation System (Omega)works to ensure direct routings is discussed The importance ofair traffic controllers understanding that speed control is far moreimportant than vectors in conserving fuel is stressed C R

A83-33625#IMPACT DAMPING AND AIRPLANE TOWINGC MATUK Lulea, Hogskola, Doctoral Thesis, 1982, 179 pResearch supported by the Forsvaret Matenelverk refs

Three problems are treated The first concerns the impact ofa linearly elastic hammer on a linearly viscoelastic plate TheLaplace transform method is used, and the results are seen ashaving application to the design of impact protection devices Thesecond problem has to do with the towing of targets by wiresduring aircraft accelerations in a straight path Again the Laplacetransform method is used, and the results can serve as conservativeestimates to avoid failure of the wire The third problem concernsthe towing of targets by wires during semicircular aircraft turnsThe results here are obtained by means of the finite differencemethod and are checked through full-scale tests These resultscan be used in predicting the target path and avoiding wire failureduring semicircular turn maneuvers C R

A83-33767FLIGHT OPERATIONS: A STUDY OF FLIGHT DECKMANAGEMENTC A OWENS New York, Van Nostrand Remhold Co, 1982,200 p

After presenting a development history of cockpit design,including pilot tasks, control devices, instrumentation, and avionics,for aircraft employing flight crews of two or more, attention isgiven to topics associated with the flight operations of moderncommercial aircraft These include pilot activities andresponsibilities (especially with respect to air traffic control, weatherconditions, and fuel and cargo loads), the distribution of flighttasks among pilot, copilot, navigator and flight engineer, and crewselection and training criteria Consideration is also given to thevariety of documents relating to aircraft operation and navigation,typical management practices in the takeoff, climb, cruise, descentand landing portions of a flight, and the unique requirements ofcritical phases of flight with respect to unfavorable weatherconditions and emergencies due to malfunction O C

A83-36042*# Dayton Univ , OhioNUMERICAL SIMULATION OF AIRFOIL ICE ACCRETIONC D MACARTHUR (Dayton, University, Dayton, OH) AmericanInstitute of Aeronautics and Astronautics, Aerospace SciencesMeeting, 21st, Reno, NV, Jan 10-13, 1983 40 p refs(Contract NAG3-65)(AIAA PAPER 83-0112)

A mathematical model of glaze and rime ice accretion on atwo-dimensional airfoil is presented The model employs standardmethods for calculating the flow field and cloud droplet trajectoriesThis data is used as input to a thermodynamic analysis of the iceaccretion process which includes liquid runback The structure ofthe model allows for dynamic updating of the droplet collectionefficiency and heat and mass transfer processes as the accretedice shape changes This results in the improved shape predictionover previously described methods Simulations made with themodel are compared to experimental results obtained for a NACA0012 airfoil in the NASA/Lewis Icing Research Tunnel Theagreement with experiment is found to be generally satisfactoryfor some cases, but a need for improvements is indicated byothers Suggestions for improvements are made Author

A83-36043*# Toledo Univ , OhioNUMERICAL SIMULATION OF ELECTROTHERMAL DE-ICINGSYSTEMSK J DE WITT, T G KEITH, D F CHAD, and K C MASIULANIEC(Toledo, University, Toledo, OH) American Institute of Aeronauticsand Astronautics, Aerospace Sciences Meeting, 21st, Reno, NV,Jan 10-13, 1983 7 p NASA-supported research refs(AIAA PAPER 83-0114)

Transient simulations of de-icing of composite aircraftcomponents by electrothermal heating have been computed forboth one and two-dimensional rectangular geometries The implicitCrank-Nicolson formulation is used to insure stability of thefinite-differenced heat conduction equations and the phase changein the ice layer is simulated using the Enthalpy method Numericalsolutions illustrating de-icer performance for various compositeaircraft blades and environmental conditions are presentedComparisons are made with previous studies and with availableexperimental data Initial results using a coordinate mappingtechnique to describe the actual blade geometry are discussed

Author

A83-36911#NET-SKIRT ADDITION TO A PARACHUTE CANOPY TOPREVENT INVERSIONG W H STEVENS Journal of Aircraft (ISSN 0021-8669), vol20, July 1983, p 578, 579


428

03 AIR TRANSPORTATION AND SAFETY

A83-36951#CONCEPTS FOR A FUTURE JOINT AIRLIFT DEVELOPMENTPROGRAMW G MOORE, JR and J F SHEA AIAA, ASCE, TRB, ATRIF,and CASI, International Air Transportation Conference, Montreal,Canada, June 1-3, 1983 4 p(AIAA PAPER 83-1591)

It is pointed out that since World War II the U S has had themost effective airlift capability in the world in both peace and warThere are, however, signs of deterioration with respect to thiscapability The U S military has had great difficulty in gamingcongressional acceptance of a timely program to modernize andimprove the U S airlift force The U S civil airlines are faced withan apparent mablity to assure continued preeminence of the U Scivil airlift structure Almost 25 years have passed since the currentU S airlift policy was approved by the President of the U S , andit is felt that a new statement of Presidential policy is needed Itis believed to be necessary for the President, with congressionalapproval, to initiate a joint civil-military program for the developmentof an efficient and effective airlift system able to serve both thenation's civil needs and the military emergency requirements

GR

A83-36952#WORLDWIDE AVIATION OUTLOOKB J ELLE (International Civil Aviation Organization, Montreal,Canada) AIAA, ASCE, TRB, ATRIF, and CASI, International AirTransportation Conference, Montreal, Canada, June 1-3, 1983 12P(AIAA PAPER 83-1597)

The paper presents forecasts of scheduled passenger andfreight traffic for the period 1982-1992 The approach and basicassumptions are described and forecast results are presented forsix major regions of the world The overall average growth ratefor scheduled passenger-kilometres over the 10-year period isforecast at 7 0 percent per annum and the rate for scheduledfreight tonne-kilometres is forecast at 7 5 percent per annum Thepaper also discusses the dependence of traffic developments onchanges in the competitive and regulatory environment and, finally,presents some statistical evidence of the importance of airlineprofitability for future traffic growth Author

GUIDANCE CONTROL SYSTEMS FOR AIRCRAFT ON AIRPORTSURFACESD M ARNTZEN (Chicago Bureau of Engineering, Chicago, IL)and M E WILFERT (Douglas Aircraft Co , Long Beach, CA) AIAA,ASCE, TRB, ATRIF, and CASI, International Air TransportationConference, Montreal, Canada, June 1-3, 1983 9 p refs(AIAA PAPER 83-1579)

Since the conduction of the first flights, aviation has beenconcerned with overcoming the effects of poor visibility Suitableapproaches for doing this during flights have been developed onthe basis of a utilization of electronic systems, such as theAutomated Radar Terminal System (ARTS-3) However,corresponding solutions have not been implemented to assist thepilot on the ground in maneuvering from the runway to the terminalIn the U S visual aids such as edge lights and center line lightsare all that are provided for the pilot Such a system cannot warnthe pilot of other aircraft in the area A ground movement controlsystem used at Heathrow is considered, along with a SurfaceTraffic Control System (STRACS) studied by the Port Authority ofNY and NJ Attention is given to surface movement guidanceneeds and recommendations for a surface guidance system TheFAA is currently deploying Airport Surface Detection Equipment(ASDE-3) to replace visual observations with an electronicpicture G R

A83-36954#USAF MOBILITY REQUIREMENTSD D BROWN (USAF, Military Airlift Command, Scott AFB, IL)AIAA, ASCE, TRB, ATRIF, and CASI, International AirTransportation Conference, Montreal, Canada, June 1-3, 1983 6p refs(AIAA PAPER 83-1588)

This paper discusses how, as a result of United States armedforces modernization and growth, the mobility requirements haveincreased much faster than our capability to deliver them to thebattlefield Various alternatives have been developed in organicmilitary capability to include roles of the Air Force Reserve andAir National Guard, as well as the significant impact of the CivilReserve Air Fleet (CRAF) to meet our national mobilityrequirements In addition, the military and civil air transportationindustry must work more closely together to increase future airtransportation capability with a minimum of cost to all interestedparties Author

N83-25683# Comptroller General of the United States,Washington, D CA STRATEGY IS NEEDED TO DEAL WITH PEAKING PROBLEMSAT INTERNATIONAL AIRPORTS24 Mar 1983 66 p(GAO/GGD-83-4, B-208444) Avail NTIS HC A04/MF A01

The role that controlling the timing of flight arrivals could playin coping with the problem of peakmg-multiple arrivals ofinternational flights within a limited time penod-which causestraveler delays in clearing the Federal inspection precess isexamined It was concluded that because of competition,international relations, and other implications of controlling thetiming of flight arrivals this course of action should only beconsidered when all else fails in coping with peaking problemsThere is a need to establish criteria for identifying current andanticipated peaking problems affecting international travelers anda concomitant need to gauge the current and potentially enhancedcapacity of the Federal inspection operations to overcome theseproblems Only then will there be a logical basis for determiningthe need to control flight arrivals as part of an overall strategy tospeed the entry of international travelers S L

N83-25684# Army Research and Technology Labs, Fort Eustis,Va Applied Technology LabsVERIFICATION TESTING OF AN AH-1S WIRE STRIKEPROTECTION SYSTEM (WSPS)L T BURROWS Dec 1982 38 p(AD-A123188, USAAVRADCOM-TR-82-D-36) Avail NTIS HCA03/MF A01 CSCL 131

The Applied Technology Laboratory conducted developmentaland performance verification tests to determine the suitability forAH-1S application of a Wire Strike Protection System (WSPS)designed and fabricated by Bristol Aerospace Limited and BellHelicopter Textron, Inc The WSPS tested consisted of an uppercutter, a telescopic sight unit deflector, a chin cutter above the20mm gun, a lower cutter, and a forward windshield deflectorUsing the NASA-Langley Research Center's Impact DynamicsResearch Facility, an AH-1S helicopter fitted with the WSPS wassubjected to pendulum swing tests into the objective wire, whichis a steel, seven-strand, 3/8-mch-diameter cable having an11,500-pound tensile strength The WSPS successfullydemonstrated its capability to sever the objective wire in all tests,during which impact velocity, impact angle, aircraft pitch attitude,and aircraft impact area were varied During the WSPS installationit was determined that some WSPS components were notnecessary, and these were not necessary, and these were excludedfrom the system tested During the test program it was concludedthat a small cutter should be added to the system to prevent awire from hanging up on the air data sensor boom, however,timing did not permit the fabrication and test of such acomponent GRA

429

03 AIR TRANSPORTATION AND SAFETY

N83-25685# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringACES II NEGATIVE GZ RESTRAINT INVESTIGATION M.S.ThesisD G LEUPP Dec 1982 103 p refs(AD-A124713, AFIT/GE/EE/82D-45) Avail NTIS HC A06/MFA01 CSCL 01C

Seven human subjects, and 5th and 95th percentile malemanikins were subjected to -Gz conditions on a man-ratedcentrifuge to test the restraint effectiveness of the ACES II restraintsystem used on the A-10, F-15, and F-16 The restraint was testedwith shoulder straps locked, unlocked, and unlocked with theaddition of a tiedown strap connected between the lap belt andthe floor A -1 Gz condition was created by inverting the centrifugecab for 30 seconds Human subjects were exposed to levels of-1 5 and -2 Gz for 20 and 10 seconds respectively by rotating thecentrifuge arm Manikins were similarly exposed to levels up to -5Gz Off-seat displacement was measured directly by a uniquespring-loaded transducer mounted in the seat pan Lap belt andtiedown strap forces, and tracking and ejection task performancewere also measured GRA

N83-25686# INFOCOM, Crawley (England)FOREIGN TECHNOLOGY ALERT - BIBLIOGRAPHY:TRANSPORTATION SAFETY Final Report, Jan. 1980 • May1982G WILKINSON 1982 50 p(PB83-101659, INFO-FT/82-03) Avail NTIS HC A03/MF A01CSCL 01B

Abstracts from the NTIS bibliographic data base relating toground and air transportation safety are presented in thiscopyrighted bibliography which describes work originating fromcountries outside the USA Most reports are in their native language,but titles are annotated to advise readers of non-English texts Aproportion of foreign language documents have author abstractsand summaries in English Major subject headings include trafficengineering and safety, accident research and investigation,hazards and accident prevention, human factors, pedestrian safety,motor vehicles, motor cycles, pedal cycles, traffic control andaviation safety, and rescue systems Each of the 19 sections iscross-referenced, there is also an author index and useful subjectindex based on major descriptors GRA

N83-26827# National Transportation Safety Board, Washington,D C Bureau of Accident InvestigationAIRCRAFT ACCIDENT REPORT: IBEX CORPORATION GATESLEARJET 23, N100TA, ATLANTA, NEAR SAVANNAH, GEORGIA,6 MAY 19828 Apr 1983 58 p refs(PB83-910401, NTSB-AAR-83-01) Avail NTIS HC A04/MF A01CSCL 01C

On May 6, 1982, at 115528 eastern daylight time (edt), whilein cruise flight on Airway J79-121 en route to Orlando, Florida,from Teterboro, New Jersey, the flightcrew of N100TA, an IBEXCorporation Gates Learjet 23, was cleared by the Jacksonville AirRoute Traffic Control Center to descend from its altitude of FlightLevel 410 to Flight Level 390 The flightcrew acknowledged theclearance, and air traffic control observed the radar target descendAbout 2 minutes later, the airplane crashed into the Atlantic Ocean,from a steep, high speed descent about 12 miles from Savannah,Georgia The air atraffic controller made several unsuccessfulattempts to contact the airplane The pilots had reported nodifficulties in any of their radio transmissions The pilot, copilot,and the two passengers on board were killed The NationalTransportation Safety Board determines that the probable causeof the accident was an uncontrolled descent from cruise altitudefor undetermined reasons, from which a recovery was not or couldnot be effected Author

04

AIRCRAFT COMMUNICATIONS AND NAVIGATION

Includes digital and voice communication with aircraft, air navigationsystems (satellite and ground based), and air traffic control

A83-35087#NEW ADVANCES IN WIDE BAND DUAL POLARIZATIONANTENNA ELEMENTS FOR EW APPLICATIONSG MONSER (Raytheon Co , Electromagnetic Systems Div , Goleta,CA) IN Antenna Applications Symposium, Monticello, IL,September 23-25, 1981, Proceedings Urbana, IL, University ofIllinois, 1982, 10 p

The present investigation is concerned with the results of aproject which was conducted to achieve multioctave integrated,dual-polarized, array elements for EW array applications A needexisted for wideband, dual-polarized arrays with a number ofproperties These properties are related to a bandwidth which isgreater than 2 octaves, certain amplitude and phase trackingspecifications, array coverage, an element efficiency of 75 percent(minimum), and an element power handling capacity of 100 wattsThe array developed to satisfy the requirements is shown in aphotograph Eight elements were, used for_developing polarizationparallel to the array, and nine elements were employed fordeveloping polarization orthogonal to the array G R

A83-35088#A RAPID-TUNING HIGH-POWER POD-MOUNTED VHFANTENNA SYSTEMB HODGSON (American Electronic Laboratories, Inc,Montgomeryville, PA) IN Antenna Applications Symposium,Monticello, IL, September 23-25, 1981, Proceedings Urbana, IL,University of Illinois, 1982, 16 p

This paper describes a high-power jamming antenna systemThe incorporation of a microprocessor in the RF coupler givesthe system a very rapid frequency-hopping capability, enabling itto be time-shared between a number of threats The antenna iselectrically very small (approaching one-twentieth of a wavelengthat the lowest operating frequency), but gives good omni-directionalpatterns up to 70 MHz The system has an instantaneous bandwidthof approximately 1 percent, and a maximum efficiency of 40percent Author

A83-35089#MULTIMODE PLANAR SPIRAL FOR DF APPLICATIONSD D CONNELL and B J LAMBERTY (Boeing Aerospace Co,Seattle, WA) IN Antenna Applications Symposium, Monticello,IL, September 23-25, 1981, Proceedings Urbana, IL, Universityof Illinois, 1982,15 p Research supported by the Boeing AerospaceCo refs

It is pointed out that the several modes available in multiarmlog-spiral antennas can be useful in wide-angle direction-findingapplications The research undertaken in connection with thepresent investigation was conducted because the available database on multiarm spirals is sparse The computations presentedwere performed by using the Wirant computer code Wirant is amoment-method code which uses constant-current basis functionswith point marching Input impedance and radiation patterns havebeen computed and compared to measured data for a 6-arm planarspiral antenna The discussed study showed that the Wirantmoments code can be used to accurately predict patterns andimpedance of all possible modes in multiarm spirals G R

430

04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A83-35090#A NETWORK FORMULATION FOR PHASED ARRAYS -APPLICATION TO LOG-PERIODIC ARRAYS OF MONOPOLESON CURVED SURFACESR J COE and D E YOUNG (Boeing Aerospace Co, Seattle,WA) IN Antenna Applications Symposium, Monticello, IL,September 23-25, 1981, Proceedings Urbana, IL, University ofIllinois, 1982, 27 p refs

In the present investigation, a combination of electromagneticmodelling techniques and network theory are used to calculatethe performance of a log-periodic monopole array containing drivenelements as well as parasitic elements The performance of severallog-periodic monopole arrays on a conducting conical surface arealso obtained by representing the conical surface as a wire meshAn impedance matrix formulation of combined antenna and feednetwork is illustrated Both antenna and feed are represented bymultiport Thevenm equivalent networks The application of networktechniques to antenna-feed system modelling is illustratedAttention is given to array geometry, the impedance matrix of anlog-periodic monopole array (LPMA), the impedance matrix of feedLPMA with parasitic elements, the radiation pattern, theperformance function, and the input impedance G R

A83-35192COMPARATIVE ANALYSIS OF A PHASE AND AN AMPLITUDEPROCESSOR FOR AMPLITUDE MONOPULSE SYSTEMSA I SINSKY and E A LEW (Bendix Corp , Communications Div ,Baltimore, MD) IEEE Transactions on Antennas and Propagation(ISSN 0018-926X), vol AP-31, May 1983, p 519-522 SponsorshipU S Department of Transportation(Contract DOT-FA01-81-C-10041)

The theoretical performance of an amplitude monopulseprocessor is compared with that of a phase monopulse processorin the presence of thermal noise Both processors use the sumand difference beam antenna model Both processors exhibit abias error at signal-to-noise ratios below 20 dB The phaseprocessor demonstrates a smaller standard deviation in the angleestimate for target angles in the vicinity of the monopulseboresight Author

A83-35273A THEORETICAL FRAMEWORK FOR ANALYSIS OF LATERALPOSITION ERRORS IN VOR JET-ROUTE SYSTEMSD A HSU (Wisconsin, University, Milwaukee, Wl) Journal ofNavigation (ISSN 0020-3009), vol 36, May 1983, p 262-268

The applicability of a second-order differential equation in thephysics of mechanical vibration is investigated as a model foraircraft lateral position errors obtained from the VOR environmentNavigational interpretations of the parameters in the modelanalogous to a vibrating mechanical system are constructedSolutions to the second-order differential equation are described,and the properties and phenomena implied by the model arediscussed In extending the theoretical reasoning, phenomenaembedded in the aggregated data are discovered Ways are alsofound to explain the most salient features «f VOR position errorsbased on the suggested model The steps required for the futureempirical confirmation, clarification, and calibration of parametervalues are outlined C R

A83-35274ON THE USE OF HEIGHT RULES IN OFF-ROUTE AIRSPACER L FORD (Royal Signals and Radar Establishment, Malvern,Worcs, England) Journal of Navigation (ISSN 0020-3009), vol36, May 1983, p 269-287 Research supported by the Civil AviationAuthority

The standard height rules applied in off-route airspace areconsidered in order to assess the degree of intrinsic safety theyprovide, that is, the reduction of conflicts without action beingtaken by pilots or ATC The standard employed is the conflictrate that would obtain if the aircraft were uniformly randomlydistributed in the height dimension and flying straight and level ontracks distributed uniformly and randomly It is shown that, unlesssignificant height-keeping errors are present, the application of

the standard rules can lead to a reduction in the intrinsic safetyAn alternative height rule ostensibly having more desirablecharacteristics is examined on the same basis C R

A83-35275COMPUTER MODEL OF A COLLISION-AVOIDANCE SYSTEMFOR AIR TRAFFIC CONTROLS MORLEIGH Journal of Navigation (ISSN 0020-3009), vol 36,May 1983, p 288-301

The investigation presented here assumes that the airbornesystem is provided with accurate information concerning the relativeposition and velocity of any other aircraft within a range of 25 nmi Attention is restricted to aircraft flying in controlled airspace,within which it is mandatory for a flight plan to be approved byATC before an aircraft is allowed to take off The computer modelis found to operate satifactonly over a wide range of potentialconflict situations The results obtained for 'converging' conflictsituations are improved if the aircraft involved both participate inthe maneuver C R

A83-35599OMEGA APPLICATION IN THE INDONESIAN REGION[UTILISATION DE L'OMEGA DAANS LA REGIONINDONESIENNE]P GUILLARD, A RENARD, and H AL2IAL (Crouzet, Valence,Drome, France) Navigation (Paris) (ISSN 0028-1530), vol 31,April 1983, p 172-182 In French

The equipment, capabilities, and performance of the Omeganavigation system for the A 300 aircraft newly delivered to theIndonesian region are detailed Complete digital control wasinstalled to be compatible with the A 300 avionics and to enhancethe otherwise bad propagation characteristics of the area Theon-board system consists of the receiver/processor, the commandand display post, and an antenna The processor contains fiveprogrammable maps and one block processor, and can handleground links furnishing heading, airspeed, wind velocity, and linkswith the autopilot The memory stores 29 waypomts in theIndonesian region, safekeeping them between two flights A controlunit allows the pilot to retrieve and program information andcommands into the processor Details of the data processingprogram are reviewed, noting the shift to real time analysis of allavailable Omega data to improve accuracy With activation of anAustralian station in 1982, good signals were received from Reunionand Japan, a medium level from Liberia, and a weak signal fromNorway, with a listening position near Djakarta being considered

MSK

A83-36122PERFORMANCE CAPABILITIES OF PHOTOGRAPHIC FLIGHTNAVIGATION AND SENSOR ORIENTATION SYSTEMS [DASLEISTUNGSVERMOEGEN VON BILDFLUGNAVIGATIONS- UNDSENSORORIENTIERUNGSSYSTEMEN]F L J H CORTEN (International Institute for Aerial Survey andEarth Sciences, Enschede, Netherlands) Bildmessung undLuftbildwesen (ISSN 0006-2421), vol 51, May 1983, p 82-102 InGerman Translation refs

Advanced methods and instruments for navigation and inflightdetermination of the elements of exterior orientation of a sensorare reviewed Basic principles and characteristics are addressed,including the physics of coupled navigation systems, of systemsfor determining positions, and of moving objects The performanceparameters of various systems are compared, including VLFOmega, microwave reflection systems, and Doppler radar Methodsof determining height above ground and sea level and of measuringdifferences in height are examined, as are methods for orientationunder a variety of external conditions Finally, issues of costeffectiveness and applicability are addressed C D

431

04 AIRCRAFT COMMUNICATIONS AND NAVIGATION

A83-36470#DESIGN FOR TESTING OF A LOW ALTITUDENIGHT-IN-WEATHER ATTACK SYSTEMK M MARCROFT (USAF, Wright Aeronautical Laboratories,Wright-Patterson AFB, OH) IN Aircraft Prototype and TechnologyDemonstrator Symposium, Dayton, OH, March 23, 24, 1983,Proceedings New York, American Institute of Aeronautics andAstronautics, 1983, p 131-133(AIAA PAPER 83-1061)

The need for system integration in the task of designing thenext generation night-in-weather (NIW) attack system for the USAir Force is examined This integration will be needed to preprocessthe large amount of diverse information necessary to carry out alow-altitude NIW attack mission in a high-threat environment andto manage the compressed time lines associated with low-altitudeattack It is noted that, if an integrated system includes flightcritical elements, it must be designed and tested to ensure that itis fail-safe through the third failure (fail op/fail op/fail safe) It isconcluded that current design criteria and testing procedures arenot sufficient to field successfully an integrated system of thistype, and that new designs that include testability from inceptionand allow for retestmg through the aircraft's operational life assystem changes are made will be required B J

N83-25688# Defense Mapping Agency Aerospace Center, StLouis, MoPRECISION NAVIGATIONAL FILW1STRIPS FOR USE IN DODAIRCRAFTR BOZICH Sep 1982 15 p(AD-A124761) Avail NTIS HC A02/MF A01 CSCL 17G

The Defense Mapping Agency Aerospace Center (DMAAC) hasbeen producing high resolution precision aircraft navigationfilmstrips since 1969 These filmstnps are used in various typeprojection systems within Department of Defense (DoD) aircraft toprovide the pilot/flight crew with a screen display of position andprogress relative to the real world in real time Superimposed onthe projected chart image is an aircraft position symbol that appearsto move across the display screen in the direction and at a speedproportionate to that being flown over the ground DMAAC hasproduced numerous filmstnps for several operational aircraft todayand is currently producing filmstnps for test and evaluation in newaircraft systems which will require support well into the 1980s

GRA

A83-36625GE'S APG-67 - FIGHTER RADAR WITH A FUTUREG WARWICK Flight International (ISSN 0015-3710), vol 123,June 11, 1983, p 1797, 1800-1802

The GE APG-67 fighter aircraft radar system is described Theradar is being installed in the F-20 fighter, and uses the X-bandand a side-looking phased-array antenna The digital pulse Dopplerradar consists of four line-replaceable units that weigh a total of270 Ib and fill 3 28 cu ft of space The four units comprise theflat-plate, slotted-array antenna, the X-band travelling wave tubetransmitter, a radar data computer, and the radar target dataprocessor Operating in the 9 7-9 9 GHz interval, the transmitterproduces a 3 5 kW peak power and 2 0 kW average power beamand requires only forced-air cooling The coherence of thelook-down pulse permits signal processing to discern movingtargets on the ground due to Doppler shifts of the returning signalGround test requirements for the first production radars include200 hr MBTF in the laboratory M S K

N83-25691# Naval Postgraduate School, Monterey, Calif Deptof Systems TechnologySH-3 HELICOPTER/GLOBAL POSITIONING SYSTEMINTEGRATION ANALYSIS M.S. ThesisR H HART Oct 1982 60 p refs(AD-A125005) Avail NTIS HC A04/MF A01 CSCL 17G

The Global Positioning System (GPS), the transmittednavigational signal, and the overall acquisition approach areexplained Navigational receiver components are functionallydescribed and the hierarchy of platform integration and capabilityis discussed Specifically explored is the integration of GPS intothe Sikorsky SH-3 Helicopter Performance comparisons of themedium versus high dynamic receiver, based solely on preliminarysimulation data, indicate that at this time the medium dynamicreceiver is the optimum configuration Elimination of he dopplerradar m lieu of the five channel receiver would only be possibleafter through over-water testing of the high dynamic set The actualvelocity accuracy of GPS receivers in a hovering helicopter is themam question yet to be answered The overall missioneffectiveness of the GPS equipped SH-3 Helicopter should besignificantly improved because of an accurate, stand-alonenavigation system Author (GRA)

N83-25687# Comptroller General of the United States,Washington, D CFAA'S PLAN TO IMPROVE THE AIR TRAFFIC CONTROLSYSTEM. A STEP IN THE RIGHT DIRECTION BUTIMPROVEMENTS AND BETTER COORDINATION ARENEEDEDGAO 16 Feb 1983 63 p(GAO/AFMD-83-34, B-206887) Avail NTIS HC A04/MF A01

A modernization plan that describes specific improvements infacilities and equipment needed in the air traffic control systemwas developed It was recommended that an integrated long rangeplan addressing all aspects of the National Airspace Systemincluding use of the Nation's airspace and airports be developedPreliminary findings from ongoing airport and airspace reviewsshould be coordinated with equipment and facility decisions in themodernization plan The modernization plan should be updated toidentify priorities, subsystem costs, and mterdependency ofprojects Other recommendations are aimed at reducing acquisitioncosts of the enroute replacement computers and strengtheningthe management and development of automation andcommunications systems to alleviate problems identified andstatisfy the increased management demands of the system S L

N83-26828# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringINVESTIGATION OF A THIRD ORDER BARO-DAMPEDVERTICLE CHANNEL OF INS M.S. ThesisA RIAZ Dec 1982 157 p refs(AD-A124882, AFIT/GE/EE/82D-55) Avail NTIS HC A08/MFA01 CSCL 17G

The optimization of the three gams of a third-order baro-inertialvertical channel has been formulated as a stochastic optimal controlproblem, with the objective of minimizing the mean squared altitudeerror due to the noise induced altitude error and a disturbance ofknown magnitude For a vehicle carrying out a TERCOM-updateimmediately following a vertical descent, and being subjected to adisturbance input to the vertical channel, optimum gams arepresented and the performance is analyzed through a simulatedflight in a Monte Carlo analysis Performance comparisons betweenthe optimized gams and the classical gains are also presentedThe results show a significant performance improvement over theclassical gams for a vehicle carrying out the TERCOM-update

Author (GRA)

432

05 AIRCRAFT DESIGN, TESTING AND PERFORMANCE

05

AIRCRAFT DESIGN, TESTING ANDPERFORMANCE

Includes aircraft simulation technology

A83-33506* California Univ , Los AngelesCOUPLED FLAP-LAG-TORSIONAL DYNAMICS OF HINGELESSROTOR BLADES IN FORWARD FLIGHTP P FRIEDMANN and S B R KOTTAPALLI (California, University,Los Angeles, CA) American Helicopter Society, Journal (ISSN0002-8711), vol 27, Oct 1982, p 28-36 Army-supportedresearch refs(Contract NSG-1578)

The aeroelastic stability and response problem of the coupledflap-lag-torsional dynamics of an isolated hingeless rotor blade inforward flight is considered Linear, quasi-steady aerodynamicsbelow stall is included The spatial dependence of the partialdifferential nonhner equations of motion is discretized using amultimodal Galerkin method The nonlinear time dependentequilibrium position (steady state response) about which theequations are linearized is obtained by solving a sequence oflinear periodic response problems (quasilmeanzation) Resultsillustrating blade behavior in forward flight for both soft-in-planeand stiff-in-plane designs are presented Quasilmeanzation providesa clear indication of the cases when nonlinear terms due tomoderate deflections are important The results indicate thatnonlmearities affect system stability much more than systemresponse This implies that for obtaining blade vibrations and loads,approximate analytical models based on linearized formulationscould be employed, whereas for determining blade stability a moreaccurate nonlinear analysis would be required Author

A83-33546#THE DASH 8 DEVELOPMENT PROGRAMC J AUSTIN (Havilland Aircraft of Canada, Ltd, Downsview,Ontario, Canada) (Flight Test Symposium, Dorval, Quebec,Canada, Mar 17, 1982) Canadian Aeronautics and Space Journal(ISSN 0008-2821), vol 29, March 1983, p 17-24

In describing the interior arrangements, it is pointed out that astandard movable bulkhead will make it possible to alter the ratioof passengers to freight The engine, the PW120 turboprop engine,was chosen with fuel efficiency a prime consideration An accountis given of the steps taken to ensure aerodynamic cleanliness forhigh cruise efficiency Strict controls on weight have held theincrease in this area to 30 Ib over one year of design developmentKevlar/nomex structures are employed through most of the interiorfurnishings and floors C R

A83-33548#CANADIAN FORCES TRACKER AIRCRAFT FULL-SCALEFATIGUE TEST AT THE NATIONAL AERONAUTICALESTABLISHMENTD L SIMPSON, G S CAMPBELL, D P WILLIAMS, G F WMCCAFFREY, J F DEWAAL, A C WALKER, and B E SHAVER(National Aeronautical Establishment, Structures and MaterialsLaboratory, Ottawa, Canada) (Canadian Symposium on AerospaceStructure and Materials, 1st, Toronto, Canada, June 15, 1982)Canadian Aeronautics and Space Journal (ISSN 0008-2821), vol29, March 1983, p 35-57 refs

A number of topics from this test are discussed A descriptionis given of the software system used for load command and systemsafety The selection of the test load spectrum using fleet countingaccelerometer data as a basis is reviewed, with attention given tothe data rejection criteria A simple whiffletree and contour boardload application system employing only four command channelsfor six servo-hydraulic actuators is discussed It is noted that thissystem has proved to be very successful from the viewpoint ofboth reliability and load distribution Large high wing aircraft presentcertain problems when tested using the 'pivoted fuselage'

configuration adopted for this test Some of these difficulties aredescribed, and recommendations are made for future tests A statusreport on the test is provided which includes details of the failuresto date and plans for the post-test analysis and tear-downinspection C R

A83-33621PERFORMANCE FLIGHT TESTINGH SMITH, ED (Pennsylvania State University, University Park,PA) Blue Ridge Summit, PA, Tab Books, Inc, 1982, 143 p

In the early stages of flight testing, the aircraft is very gentlymaneuvered to determine its degree of stability and control Oncethe aircraft is proved to perform safely, it is carefully tested tosee if it meets the performance that was expected of it when itwas designed This procedure is, therefore, appropriately termed,'performance flight testing' This book describes a series of testsby which most of the performance information normally requiredfor aircraft operation can be obtained The tests are designed tobe carried out by the average light aircraft pilot or someone withequal aviation background No special equipment is required otherthan a stopwatch and a basic electronic calculator Attention isgiven to the effects of the atmosphere, general flight testprocedures, airspeed calibration, stall speed, takeoff performance,climb performance, cruise performance, and descent and landingperformance G R

A83-33627TECHNOLOGY STATUS FOR AN ADVANCED SUPERSONICTRANSPORTW T ROWE (Douglas Aircraft Co, Long Beach, CA) Society ofAutomotive Engineers, West Coast International Meeting, SanFrancisco, CA, Aug 16-19, 1982 9 p refs(SAE PAPER 820955)

An assessment is undertaken of the development status of aproprietary SST propulsion, structural design, materials, andaerodynamics research program The Mach 2 2-cruise speed SSTdesign considered incorporates a novel wing planform which resultsin a 45 percent lift-to-drag ratio improvement over the ConcordeSST, and employs superplastic forming and diffusion bondingmethods in the fabrication of a 78 percent Ti alloy structureComposites are used in all secondary structures A reoptimizationof the engine cycle, which includes variable features, improvesfuel efficiencies in the subsonic cruise regime It is noted that jetnoise suppression techniques are able to keep noise levels downto those of wide-bodied subsonic transports O C

A83-33628* National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifAPPLICATIONS OF ADVANCED UPPER SURFACE BLOWINGPROPULSIVE-LIFT TECHNOLOGYJ A COCHRANE, D W RIDDLE (NASA, Ames Research Center,Quiet Short-Haul Aircraft Office, Moffett Field, CA), and S YOUTH(Boeing Commercial Airplane Co , Preliminary Design Dept, Seattle,WA) Society of Automotive Engineers, West Coast InternationalMeeting, San Francisco, CA, Aug 16-19, 1982 13 p(SAE PAPER 820956)

The success of the Quiet Short-Haul Research Aircraft led tostudies of this technology for a business jet and a Short-HaulTransport The studies showed that the Short-Haul Transport couldoperate from a 762 0-m runway with 95 passengers at low noiselevels Design range was 500 n mi but with maximum fuel loadthe runway length is only increased to 883 9 m while the range isincreased to more than 1000 n mi Two business jet designswere studied, one design was based on a 457 2-m field lengthand the other was designed for a 760 0-m field length The businessjet designed for a 457 2-m field length can also be loaded tomaximum fuel capacity In this case the range increases from 500n mi to 1400 n mi while the runway length increases from457 2 m to 632 5 m The business jet studies showed that theapplication of advanced propulsive-lift technology to this classaircraft can result in payload-range-speed performance comparableto current aircraft with about one-half the runway lengthrequirement Author

433


A83-33629PROP-FAN POWERED AIRCRAFT - AN OVERVIEWS G LUDEMANN (United Technologies Corp , Hamilton StandardDiv, Windsor Locks, CT) Society of Automotive Engineers, WestCoast International Meeting, San Francisco, CA, Aug 16-19, 198211 p refs(SAE PAPER 820957)

The design features and performance characteristics of prop-fanrotors are considered in light of fuel consumption reductionrequirements, with attention to the development status of prop-fantechnology being investigated at NASA-Lewis, NASA-Ames, andNASA-Dryden Flight Test Center The aircraft types for whichprop-fans are being considered are short and medium rangepassenger aircraft, large cargo aircraft, and military patrol aircraftEmphasis is given to performance studies concerned withpropulsion efficiency, far field and aircraft interior noise levels,and block fuel savings O C

A83-33952MATERIALS IN THE MIRROR OF AVIATION CRITERIA[WERKSTOFFE IM SPIEGEL DER LUFTFAHRTKRITERIEN]E LOECHELT (Veremigte Flugtechnische Werke GmbH, Bremen,West Germany), H KELLERER (Messerschmrtt-Boelkow-BlohmGmbH, Ottobrunn, West Germany), and L BRENNER (DormerGmbH, Friednchshafen, West Germany) IN Highly stressedmaterials, with aviation considered as an example Oberursel,West Germany, Deutsche Gesellschaft fuer Metallkunde, 1982, p3-31 In German

A primary consideration in the aviation industry with respect tomaterials and structural design is related to an employment ofmaterials having minimum weight and providing a high safety levelThe present investigation is concerned with individual strengthcriteria and the use of specific materials for applications relatedto the aircraft structure A number of European aircraft of currentinterest are considered, taking into account a short-range transportaircraft for 15 passengers, a multipurpose helicopter using glassfiber-reinforced plastic materials for the rotor blades, the militaryaircraft Tornado with a structural section made largely of titanium,a medium-range military transport aircraft, the Airbus A310, andthe Alpha Jet which uses carbon-fiber reinforced plastic Attentionis given to the economics of a use of novel light materials, safetycriteria, aluminum materials, an evaluation of titanium alloys,examples for an employment of steel, and the prospects offeredby fiber-reinforced materials G R

A83-34312THE RESPONSE OF AIRCRAFT TO PULSE EXCITATIONP K R BHARGOV and H R SRIRANGARAJAN (AeronauticalDevelopment Establishment, Structures and Materials Div,Bangalore, India) Computers and Structures (ISSN 0045-7949),vol 17, no 3, 1983, p 335-338

The response of aircraft and landing gear, idealized as atwo-degree of freedom nonlinear system, to pulse excitation isanalyzed using the Runge-Kutta algorithm In addition, theapplication of a microcomputer for analyzing nonlinear vibrationproblems is evaluated Results show that the response decreasesas the value of epsilon increases, where epsilon is anonlinear-spring parameter It is demonstrated that amicrocomputer is useful in analyzing these types of problems,even though it is slow, since it eliminates turn around time N B

A83-35138*MICROPROCESSOR-BASED OPTIMAL CONTROLLERS FOR AHELICOPTER TURRET CONTROL SYSTEMN COLEMAN (U S Army, Armament Research and DevelopmentCommand, Dover, NJ) and N K LOH (Oakland University,Rochester, Ml) IN Annual Allerton Conference on Communication,Control, and Computing, 19th, Monticello, IL, September30-October 2, 1981, Proceedings Urbana, IL, University of Illinois,1982, p 659-668 refs

The design and implementation of microprocessor-baseddiscrete-time optimal controllers for the XM-97 helicopter gun-turretcontrol system is considered Nonfirmg and firing test results are

presented Significant performance improvement of the optimalturret over the original turret has been obtained in terms of percentovershoot, settling time, and shot pattern dispersion Author

A83-35315CF34 UPGRADES CHALLENGER CAPABILITIESD M NORTH Aviation Week and Space Technology (ISSN0005-2175), vol 118, May 16, 1983, p 63-65, 69

The evaluation of flight performance presented here is basedon a comparison between the new Challenger CL-601 and theChallenger CL-600 It is noted that the drawback to the 600 hadto do with range, not with overall handling characteristics, whichare considered excellent Flying at a long-range cruise of Mach0 74 and its higher 42,250-lb gross weight, the range of theChallenger 601 is approximately 3500 n mi The Challenger 601sall have the fuselage fuel tank installed during production Withthis tank, the fuel capacity is increased from 14,900 Ib to 16,725Ib The most obvious difference between the two models is theinstallation of 4-ft wmglets on the newer aircraft These wmgletsafford a cruise efficiency increase of 3-4 percent Another importantchange is the engine nacelles on the 601 The interior dimensionsof the two models are identical It is pointed out that the 601'sauxiliary power unit was moved forward to counter some of theadditional weight of the CF34 engines C R

A83-35623SAAB-FAIRCHILD 340 - TRANSATLANTIC FRONTRUNNERAir International (ISSN 0306-5634), vol 24, June 1983, p 267-271,272, 274, 295

A discussion is presented concerning the aircraft design andconstruction program management arrangements devised by twoaircraft manufacturers, Saab-Scama of Sweden and FairchildIndustries of the U S, in order to produce the Saab-Fairchild 340regional airliner This aircraft employs two 1630-shp turbopropengines and seats 30-40 passengers Significant use is made ofmetal-to-metal and aluminum honeycomb bonding, together withsandwich composite materials Use is also made of a fuly digital,fail-passive Flight Guidance and Autopilot system which employsdual microprocessor computations The low wing, which has anaspect ratio of 11, is based on a novel NASA airfoil profile whichyields improved lift/drag ratios in takeoff and climb together withreduced cruise drag O C

A83-35624AIRCRAFT DESIGN PHILOSOPHY. I - LEE BEGIN OFNORTHROPR BRAYBROOK Air International (ISSN 0306-5634), vol 24,June 1983, p 296-302

Contemporary tactical aircraft designers must be able toconsider not only novel design possibilities in their work, but alsoperformance requirements that include, in addition to performancedemands, reliability and maintenance manpower figures In addition,attention must be given to pricing policy regarding the recovery ofdevelopment funds, and to offset programs that restrict the impactof a given system's purchase on the balance of payments of therecipient nation The F-5/F-20 and F-18 development programsare taken as exemplary cases of these rules Consideration isgiven to trends in such fighter aircraft performance factors asrate of climb, thrust/weight ratio, maximum instanteous turn rate,and maximum payload as a ratio of takeoff weight The mostimpressive current aircraft in these respects are the F-16, F-18,F-20, and Mirage 2000 O C

A83-35772#BRING COHESION TO HANDLING-QUALITIES ENGINEERINGR H HOH (Systems Technology, Inc, Hawthorne, CA)Astronautics and Aeronautics (ISSN 0004-6213), vol 21, June1983, p 64-69 refs

Handling-quality deficiencies afflicting aircraft representproblems which are difficult to deal with This difficulty is largelyrelated to the dependence of handling-quality evaluations on aninterpretation of pilot rating data The present investigation providesan interpretation of the process of developing flying-quality criteria

434


and its problems 'Handling qualities' are defined as 'characteristicsof a vehicle which make it satisfactory, adequate, or inadequatein terms of its response to control by a human operator in thepresence of varying levels of atmospheric disturbances and outsidevisual cues' Pilot opinion is quantified from a decision-tree typeof rating scale The relations of this scale, called the Cooper-Harperpilot rating, to the considered definition are examined It is foundthat the assurance of good handling qualities for modern aircraftrequires a combination of unified analysis and experimentaltechniques combined with excellent communication among flighttest engineers, pilots, and other persons involved G R

A83-35947FULL-SCALE MEASUREMENTS OF BLADE-VORTEXINTERACTION NOISED A BOXWELL and F H SCHMITZ (U S Army, AeromechanicsLaboratory, Moffett Field, CA) American Helicopter Society,Journal (ISSN 0002-8711), vol 27, Oct 1982, p 11-27 refs

Full-scale far-field acoustic data on four different two-bladedrotors encountering blade-vortex interaction are compared TheUH-1H helicopter was tested with its standard NACA 0012 airfoilrotor Data are also presented for the AH-1S helicopter configuredwith its standard 540 rotor, the Kaman K747 rotor, and the OGEEtip rotor The data were reduced using 'time-windowing' of theimpulsive noise event, thus enhancing the signal-to-noise ratio ofthe in-flight data Strong pressure gradients, isolated in the UH-1Hand AH-1S 540 rotor signatures, strongly influenced the subjectiveannoyance of the rotor The peak amplitudes and power spectrumof the K747 and OGEE rotors were about equal and generatedless annoyance than the standard AH-1S or UH-1H rotors

Author

A83-35948* California Univ , Los AngelesCOUPLED FLAP-LAG-TORSIONAL DYNAMICS OF HINGELESSROTOR BLADES IN FORWARD FLIGHTP P FRIEDMANN and S B R KOTTAPALLI (California, University,Los Angeles, CA) American Helicopter Society, Journal (ISSN0002-8711), vol 27, Oct 1982, p 28-36 Army-supportedresearch refs(Contract NSG-1578)

The results presented in connection with the currentinvestigation are based on a relatively comprehensive analysis ofthe coupled flap-lag-torsion dynamics of an isolated hingeless rotorblade in forward flight Two elastic modes for each of the flap, lag,and torsion degrees of freedom were used A convenient numericalmethod is implemented for obtaining the nonlinear periodic bladeresponse It is concluded that the presented numerical methodsprovide a very effective means for determining both aeroelasticstability and response Quasi-lineanzation gives a clear indicationof the cases when nonlinear terms due to moderate deflectionsare important It is found that these terms can be both stabilizingand destabilizing Forward flight seems to be stabilizing the bladefor a considerable number of cases considered, particularly whenthe blade is soft-in-plane G R

A83-35949A TUBULAR BRAIDED COMPOSITE MAIN ROTOR BLADESPARM L WHITE (Kaman Aerospace Corp , Bloomfield, CT) AmericanHelicopter Society, Journal (ISSN 0002-8711), vol 27, Oct 1982,p 45-48 refs

In connection with efforts to enhance helicopter bladeoperational chractenstics and to reduce manufacturing costs, thepreliminary design and process development was undertaken of acomposite improved mam rotor blade for the OH-58 helicopterThis design is unique in that the blade spar is fabricated bymechanical tubular braiding Mechanical braiding is an establishedtextile process for weaving a tubular fabric which has beenemployed for more than a century in fabricating products such arope, hose, and cable assembly overlays Recently, it has beenadapted to composite fabrication, predominantly in light duty ornonstructural applications such as aircraft ducting Attention is givento the technical approach, the blade configuration, development

testing, and costs It is concluded that mechanical braiding is aviable manufacturing technology for helicopter ma.m rotor bladespars This technology will permit significant manufacturing costreduction G R

A83-35950EVALUATION OF THE EFFECT OF VOIDS IN COMPOSITE MAINROTOR BLADESD G OR LI NO (U S Army, Applied Technology Laboratory, FortEustis, VA), R J SHUFORD, and W W HOUGHTON (U S Army,Army Materials and Mechanics Research Center, Watertown, MA)American Helicopter Society, Journal (ISSN 0002-8711), vol 27,Oct 1982, p 49-56

The design and fabrication of the Improved Mam Rotor Blade,designated K-747, as a replacement for the Bell Model AH-1SCobra, was undertaken in connection with mission requirementsnecessitating higher armament payloads, and, thus, a need toimprove rotor lifting capacity The required 6-percent increase inhover gross weight appeared to be obtainable by replacing themam rotor blades with new blades having increased aerodynamicefficiency In order to assess void growth in composite mam rotorblades, it was thought desirable to subject one K-747 mam rotorblade to 28 million cycles (1440 flight hours) of spectrum testingIf no sign of degradation or void growth occurred, a reasonablelevel of confidence in the structural integrity of the blade could beestablished Attention is given to a specimen description, theapplication of fatigue loads, the conducted fatigue test, and theemployed nondestructive inspection techniques G R

A83-36065LIGHT AIRCRAFT AND SAILPLANE STRUCTURES INREINFORCED PLASTICSR TETLOW Materials and Design (ISSN 0261-3069), vol 4,Feb-Mar 1983, p 657-662 refs

Newer materials for the aircraft designer include those utilizingcarbon fiber in its various forms and, to a lesser extent, KevlarThese materials, with high specific strength (ultimatestrength/density) and high specific stiffness (modulus/density) offerspecial possibilities for the aircraft designer However, the cheaper,less structurally attractive glass is the material which has beenmost widely used This is particularly true in the case of sailplanesUnidirectional reinforced plastic structural materials are comparedwith Sitka Spruce and an aluminum alloy Wing structures, fuselagestructures, and control surfaces are considered Attention is givento the shear moduli for various materials, the optimum stress levelsfor simply supported compression panels, the optimum stress levelsfor a wide column compression panel, and wing loading levels

GR

A83-36074THE HISTORY OF V/STOL AIRCRAFTJ J SCHNEIDER (Boeing Vertol Co , Philadelphia, PA) Vertifhte(ISSN 0042-4455), vol 29, Mar-Apr 1983, p 22-29

The development of VTOL and STOL aircraft, excludinghelicopters, is traced from its beginnings through the early 1950'sThe general classification of these aircraft in terms of thrustgeneration and of conversion from lift to cruising mode is presented,and the capabilities desired in a V/STOL aircraft are consideredThe evolution of V/STOL concepts, designs, and prototypes fromantiquity through the infancy of powered flight to the 1940's and1950's is recounted, including discussion of the work of Sikorskyand of Focke-Wulf in the late 1930's and early 1940's, the USNavy POGO-VTOL program in the 1950's, the Army XV-1, 2, and3 and Air Force X-13 and 14 aircraft, and the British Short SC 1

TK

A83-36075THE SUPER STALLIONS P KRUEGER (United Technologies Corp, Sikorsky Aircraft,Stratford, CT) Vertifhte (ISSN 0042-4455), vol 29, Mar-Apr1983, p 30-32, 41

The design features of the U S Navy/Marine Corps CH-53E(super stallion) helicopter are presented Modifications undertaken

435


in the previous design, the CH-53D, to increase payload from20,000 to 32,000 pounds include the addition of a third T-64-typeengine, a seven-blade, 79-foot-diameter rotor employing ahigh-stress Ti spars, a tail-pylon and tail-rotor configuration tilted20 deg to port to provide both vertical and horizontal thrust, anew dual digital automatic flight-control system, and improvedhydraulics Navy and Marine Corps operational requirements,including an airborne minesweeping configuration, MH-53E, arediscussed T K

A83-36204#SIMULATOR FIDELITY AND FLIGHT TEST DATA - IMPROVINGTHE FLIGHT PERFORMANCE OF THE B-52H WSTPRODUCTION UNIT FLIGHT STATION SIMULATORD A SCAFETTA (Singer Co, Link Flight Simulation Div,Binghamton, NY) IN Flight Simulation Technologies Conference,Niagara Falls, NY, June 13-15, 1983, Collection of Technical Papers

New York, American Institute of Aeronautics and Astronautics,1983, p 1-13 refs(AIAA PAPER 83-1075)

A systematic method of analysis for comparing aircraft simulatorflight performance against actual aircraft flight test data is presentedas a means of improving the fidelity of the B-52H WST ProductionUnit Flight Station Simulator Verification of simulated aircraftperformance as designed to reflect an airframe manufacturer'sdata package is established against flight test data as containedin the aircraft's Category II flight test report and flight performancemanual Discussions are included on the design approaches usedfor the mathematical modeling of the engine and aerodynamicsimulation models as an introduction to the data analysis methodFirst, a detailed analysis of all available engine and aircraft flighttest data is made Second, simulated engine performance isverified Third, simulated aircraft performance for the 'clean' aircraftconfiguration is verified Finally, a simulated aircraft performancefor the 'dirty' aircraft configuration is verified by analyzing eachaircraft drag component separately Based on the analysis, severalengine and aerodynamic simulation model changes were made tothe original design As a result, the flight performance of the B-52HWST Production Unit Flight Station Simulator matches aircraft flighttest data Author

A83-36206*IN-FLIGHT SIMULATION AT THE U S. AIR FORCE AND NAVALTEST PILOT SCHOOLSL KNOTTS and M PARRAG (Calspan Advanced TechnologyCenter, Buffalo, NY) IN Flight Simulation TechnologiesConference, Niagara Falls, NY, June 13-15, 1983, Collection ofTechnical Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 23-31 refs(AIAA PAPER 83-1078)

The earliest variable stability aircraft were created during themid 1940's These aircraft, also known as in-flight simulators, haveevolved from the original F4U Corsair with a servo controlledauxiliary rudder, to the USAF Total In-Flight Simulator, which has6-degree of freedom simulation capability In-flight simulation wasfirst used as a training tool at the U S Naval Test Pilot School in1960 In 1963, in-flight simulation was added to the U S Air ForceTest Pilot School curriculum All the variable stability aircraft usedat the Test Pilot Schools are equipped with two sets of cockpitcontrols One set is used by the safety pilot, while the studenttest pilot or 'evaluation pilot' uses the second set A brief descriptionis provided of each in-flight simulator currently used at the Navaland Air Force Test Pilot Schools Attention is also given to thevariable stability flight program, and special projects performed byeach class in addition to the routine variable stability flights

GR

A83-36211*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifSPECTRAL DECONTAMINATION OF A REAL-TIMEHELICOPTER SIMULATIONR E MCFARLAND (NASA, Ames Research Center, Moffett Field,CA) IN Flight Simulation Technologies Conference, Niagara Falls,NY, June 13-15, 1983, Collection of Technical Papers New York,American Institute of Aeronautics and Astronautics, 1983, p64-70(AIAA PAPER 83-1087)

Nonlinear mathematical models of a rotor system, referred toas rotating blade-element models, produce steady-state,high-frequency harmonics of significant magnitude In a discretesimulation model, certain of these harmonics may be incompatiblewith realistic real-time computational constraints because of theiraliasing into the operational low-pass region However, the energyis an aliased harmonic may be suppressed by increasing thecomputation rate of an isolated, causal nonlmearity and using anappropriate filter This decontamination technique is applied toSikorsky's real-time model of the Black Hawk helicopter, as suppliedto NASA for handling-qualities investigations Author

A83-36205#INDOCTRINATION OF NAVY TEST PILOTS TO VECTOREDTHRUST FLIGHT IN THE X-22A IN-FLIGHT SIMULATORJ L BEILMAN (Calspan Advanced Technology Center, Buffalo,NY) IN Flight Simulation Technologies Conference, Niagara Falls,NY, June 13-15, 1983, Collection of Technical Papers New York,American Institute of Aeronautics and Astronautics, 1983, p14-22 refs(AIAA PAPER 83-1076)

A series of flight demonstrations has been conducted with theNavy X-22A V/STOL Research Aircraft at Buffalo, NY The purposeof the demonstrations is to introduce selected U S Naval TestPilot School (TPS) student pilots to the use of thrust-vectoring asa means of flight control Beginning in 1981, the faculty of theNavy TPS designated four pilots from each TPS class to participatein the X-22A demonstration program Main elements of the NavyTPS/X-22A Special Project include a ground school on the X-22A,ground-based simulation using the X-22A itself coupled to asix-degree-of-freedom digital computer model, a one-hour flightunder visual meteorological conditions, and a one-hour flight undersimulated instrument meteorological conditions, using theHead'Up-Display and Microwave Landing System Attention is givento details regarding these elements, the provided lectures, and anevaluation of the results obtained with the program G R

A83-36214#ERROR SOURCES IN HYBRID COMPUTER BASED FLIGHTSIMULATIONR A WEEKS (Northrop Corp, Pico Rivera, CA) IN FlightSimulation Technologies Conference, Niagara Falls, NY, June13-15, 1983, Collection of Technical Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 84-91(Contract F33615-78-C-3608)(AIAA PAPER 83-1090)

Man-in-the-loop real time simulation, with a sophisticatedsimulator, requires a large computation facility to provide thecapability for effective and detailed mathematical modeling of theair vehicle and its subsystems Analog and digital computers canbe employed for the performance of the required calculationsEach computer type has certain advantages and drawbacks Manylarge simulation mechanizations run, therefore, in a hybrid fashion,where both analog and digital computing methods are employedThe present investigation is concerned with errors and problemsassociated with both types of computation, taking into accountalso the communication link between analog and digitalcomputations Typical errors encountered in analog, digital, andhybrid computation are listed in a table A linear airframe modelwas utilized for the study of the effects of error sources on solutionaccuracy G R

436


A83-36215#USE OF FLIGHT TEST RESULTS TO IMPROVE THE FLYINGQUALITIES SIMULATION OF THE B-52H WEAPON SYSTEMTRAINERJ WEISS (Singer Co, Link Flight Simulation Div, Binghamton,NY) IN Flight Simulation Technologies Conference, Niagara Falls,NY, June 13-15, 1983, Collection ol Technical Papers New York,American Institute of Aeronautics and Astronautics, 1983, p92-113 refs(AIAA PAPER 83-1091)

Correlating simulation results to flight test results proved to bea useful tool in assuring high-fidelity flight simulation for the B-52HWeapon System Trainer The particular correlation described inthis paper was limited to the longitudinal flying qualities Analysespertaining to the simulation of the engine, aircraft performance,and lateral-directional flying qualities were performed prior to thecorrelation The correlation demonstrated the significance of fuelloading and fuel slosh on certain flight test maneuvers It resultedin modifications to the design data pitching moment coefficientequation and stabilizer angle design These modifications improvedthe simulation results to the point where they closely matchedwith the flight test results Author

A83-36225#FLIGHT FIDELITY TESTING OF THE F/A-18 SIMULATORST C SANTANGELO (U S Navy, Naval Air Test Center, PatuxentRiver, MD) and R T GALLOWAY (US Navy, Naval TrainingEquipment Center, Orlando, FL) American Institute of Aeronauticsand Astronautics, Flight Simulation Technologies Conference,Niagara Falls, NY, June 13-15, 1983 7 p refs(AIAA 83-1094)

The development program for the first operational flight trainer(OFT) for the Navy F/A-18 aircraft is described, with a focus onflight-fidelity testing The problems inherent in constructingspecifications and beginmg development before the configurationand flight characteristics of the F/A-18 were finalized are discussedThe OFT design includes actual cockpit controls, a 3-wmdow,120x30-deg visual display driven by 3-channel VITAL-IV CGIsystem, a g-seat/g-suit/seat-shaker motion-cueing system, aninstructor/operator station, and a host computer consisting of fourSEL 32/77 CPU incorporating real-time input/output capability Thetechniques used to test the flight fidelity of the OFT are outlined,and the importance of quick access to flight-test results, pilotinput, comprehensive database construction, and the use of definedtest parameters is emphasized Future improvements such asautomatic fidelity-testing functions built into the OFT and automaticdata recording are proposed The designs of the weapons-tacticstrainer and part-task trainer for the F/A-18 are also considered

TK

A83-36234*# Boeing Commercial Airplane Co , Seattle, WashPROGRESS IN PROPULSION SYSTEM/AIRFRAMESTRUCTURAL INTEGRATIONJ L WHITE, T L JANSSEN, and T F YANTIS (Boeing CommercialAirplane Co , Seattle, CA) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 9 pNASA-sponsored program refs(AIAA PAPER 83-1123)

Attention is given to the improvements in mathematicalmodeling, and the emerging role of computer-related technology,in airframe structural technology advancements related to theengine/airframe integration requirements of such recent designsas the 747 airliner's JT9D turbofan engine nacelle Also notedare investigation results concerning propulsion system flight loadsand theinnfluence on thrust-specific fuel consumption deterioration,which has been addressed through the development of the novelstructural concept of the 'load-carrying core cowl' engine nacellestructure Analytical studies on integrated system vibration includelow frequency, nonsynchronous vibration analyses of large, highbypass turbofan engines that have been conducted by means ofthree-dimensional integrated finite element models O C

A83-36285*# Lockheed-Georgia Co , MariettaAERODYNAMIC DESIGN OF PROPFAN POWEREDTRANSPORTSA S ALJABRI (Lockheed-Georgia Co , Marietta, GA) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 12 p refs(Contract NAS2-11120)(AIAA PAPER 83-1213)

A case study is presented of the design of efficient propfantransport aircraft configurations, employing standard subsonic andtransonic computed codes that have been modified to accountfor slipstream effects After numerically simulating theaerodynamics of the interaction of the wing/nacelle configurationwith the swirling slipstream, interference effects are assessed anddesign procedures are provided which may reduce adverseinterference phenomena These procedures are demonstrated forthe case of the design of a Mach 0 8-cruise turboprop aircraft

OC

A83-36406*# Goodyear Aerospace Corp , Akron, Ohio1983 LTA TECHNOLOGY ASSESSMENTR L ASHFORD (Westmghouse Electric Corp, TCOM, Columbia,MD), R G E BROWNING (Goodyear Aerospace Corp, Akron,OH), B B LEVITT (Summit Research Corp, Gaithersburg, MD),N J MAYER (NASA, Washington, DC), and D E WOODWARD(Association of Balloon and Airship Constructors, Alexandria, VA)American Institute of Aeronautics and Astronautics, Annual Meetingand Technical Display, Long Beach, CA, May 10-12, 1983 44 prefs(AIAA PAPER 83-1617)

Several aspects of LTA (lighter-than-air) technologydevelopment are reviewed Technological developments ofclassical airships through 1974 are examined A brief historicaland technological summary of five specialized LTA equipmentconcepts is presented metal-clad airships, free balloons,semibuoyant vehicles, high-altitude platforms, and tetheredaerostats Current LTA technology developments are reviewed withparticular emphasis on VTOL airships capable of heavy lift andon long endurance types for coastal maritime patrol Finally, thefuture prospects of LTA system development are considered withattention given to manned conventional and hybrid vehicles,tethered vehicles, and RPVs B J

A83-36448THE KA-26 HELICOPTER [VERTOLET KA-26]N F SURIKOV, G I IOFFE, A A DMITRIEV, and E G PAKMoscow, Izdatel'stvo Transport, 1982, 224 p In Russian

Basic technical data on the design and flight characteristics ofthe multipurpose Ka-26 helicopter are presented Particularconsideration is given to the cabin design, the hydraulic system,the powerplant, the control system, and the fuel systemApplications of the helicopter are discussed (e g , load transport,forest patrol, ship use), and support systems are considered

BJ

A83-36460#XB-70 TECHNOLOGY ADVANCEMENTSJ W ROSS and D B ROGERSON (Rockwell International Corp ,El Segundo, CA) IN Aircraft Prototype and TechnologyDemonstrator Symposium, Dayton, OH, March 23, 24, 1983,Proceedings New York, American Institute of Aeronautics andAstronautics, 1983, p 19-38(AIAA PAPER 83-1048)

Attention is given to the technological advancements inaerodynamics, structural design, and control systems, which wereincorporated in the XB-70 in order to meet performancerequirements The bomber's unique configuration comprised atwo-position windshield, a canard for pitch control and trim, alarge planform delta wing with 'elevens' (elevator/ailerons) forsimultaneous pitch and roll control, folding wing tips, variable engineair inlet geometry, and a coordination of the engine inlet wedgeshock with the delta wing's geometry to generate 'compressionlift' The structural concept of the XB-70 employed, in addition to

437


stainless steel honeycomb construction, elements of titanium andtool steel Aircraft systems employed high temperature, highpressure hydraulic components and high temperature, high altitudeac electrical components O C

A83-36461#VARIABLE SWEEP WING DESIGNR W KRESS (Grumman Aerospace Corp, Bethpage, NY) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 43-61(AIAA PAPER 83-1051)

The evolution of variable sweep aircraft design is traced fromits beginnings in Germany near the end of World War II throughUS applications culminating in the sophistication of the F-14 systemHeaviest treatment is given the F-14, most familiar to the author,and wherein variable sweep was 'worked' the hardest Foreignapplications are also discussed briefly Author

A83-36462#THE APPLICATION OF LOW-COST DEMONSTRATORS FORADVANCEAD FIGHTER TECHNOLOGY EVALUATIONG ROSENTHAL and G BRANDEAU (Fairchild Republic Co ,Farmmdgale, NY) IN Aircraft Prototype and TechnologyDemonstrator Symposium, Dayton, OH, March 23, 24, 1983,Proceedings New York, American Institute of Aeronautics andAstronautics, 1983, p 63-71(AIAA PAPER 83-1052)

A demonstrator aircraft, which unlike a prototype need notmatch the size, construction, systems, functions, specifications andperformance envelope of a prospective production aircraft, isdesigned to provide high quality, systematic flight research datawhich can support the design and development of future aircraftat reduced risk In order to control the costs associated with thedevelopment of next-generation fighter aircraft, it is desirable thatmany competing system and concept categories be evaluatedThis may be achieved through the application of principles andprogram approaches that can reduce individual demonstratorprogram costs Attention is presently given to recent experiencewith a subscale flight demonstrator constructed with a view to thedevelopment of the Next Generation Trainer Aircraft O C

A83-36465#AEROSPACE TECHNOLOGY DEMONSTRATORS/RESEARCHAND OPERATIONAL OPTIONSA C DRAPER, M L BUCK, and D R SELEGAN (USAF,Aeromechanics Div, Wright-Patterson AFB, OH) IN AircraftPrototype and Technology Demonstrator Symposium, Dayton, OH,March 23, 24, 1983, Proceedings New York, American Instituteof Aeronautics and Astronautics, 1983, p 89-102 refs(AIAA PAPER 83-1054)

Attention is given to flight demonstrator programs relevant tothe identification of designs which promise to bridge the gapbetween such current space vehicle programs as the Space Shuttleand the future Maneuverable Reentry Research Vehicle, AdvancedMilitary Space Capability Vehicle, and the evolving family ofTransatmosphenc Vehicles These flight tested demonstratorvehicles have yielded useful design data concerning operationalflexibility, integration and subsystem requirements, heat shieldperformance, crossrange maneuvering, accurate guidance torecovery point, weight minimization, and advanced materials andstructures O C

A83-36466#YAV-8B FLIGHT DEMONSTRATION PROGRAMK V STENBERG (McDonnell Aircraft Co, St Louis, MO) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 103-112(AIAA PAPER 83-1055)

The AV-8B Harrier II vertical and short takeoff and landing(V/STOL) aircraft is the product of over 25 years of developmentIt effectively combines the proven vectored thrust concept of the

AV-8A and its antecedents with modern U S technology Significantadvances in aerodynamics, propulsion, structures and avionics havebeen incorporated into the AV-8B to double its payload-radiuscapability over the AV-8A and improve its operational readinessand effectiveness These technologies were first incorporated intothe YAV-8B prototype aircraft and demonstrated through a flighttest program, providing a sound technical basis for AV-8B fullscale development and subsequent production programs Author

A83-36467#THE F-16 - A TECHNOLOGY DEMONSTRATOR, A PROTOTYPE,AND A FLIGHT DEMONSTRATOR.H J HILLAKER (General Dynamics Corp, Fort Worth, TX) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 113-120(AIAA PAPER 83-1063)

Attention is given to the YF-16 Lightweight Fighter prototypeprogram's demonstration of emerging design possibilities TheYF-16 is also compared to the F-16 Advanced Fighter TechnologyIntegration aircraft, which is demonstrating additional technologiesunder a more conventional set of program characteristics TheYF-16 integrated such innovative design features as a blendedwing/body configuration, controlled vortex flow-induced lift,fly-by-wire control, relaxed static stability, automatically variablecamber, and a high-g cockpit design for high speed maneuveringAn additional F-16 research variant, the F-16XL flight demonstrator,incorporates a large area cranked arrow wing planform whichpromises significant performance gams beyond those of currentF-16s OC

A83-36468*AFTI/F-111 MISSION ADAPTIVE WING TECHNOLOGYDEMONSTRATION PROGRAMR HARDY (Boeing Military Airplane Co , Wichita, KS) IN AircraftPrototype and Technology Demonstrator Symposium, Dayton, OH,March 23, 24, 1983, Proceedings New York, American Instituteof Aeronautics and Astronautics, 1983, p 121-126(AIAA PAPER 83-1057)

The use of smooth, continuously variable camber leading andtrailing edges controlled by digital computers can improve therange-payload, maneuverability, and platform stability of newairplanes A NASA Dryden F-111 is being modified to demonstratethis technology under an Air Force Flight Dynamics Laboratorycontract The demonstration program has identified and solveddetailed engineering problems and developed new automatic flightcontrol modes Author

A83-36469#X-29 INTEGRATED TECHNOLOGY DEMONSTRATOR ANDATFG SPACHT (Grumman Aerospace Corp, Bethpage, NY) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 127, 128(AIAA PAPER 83-1058)

The technologies included in the X-29 are discussed, andattention is given to how these technologies may benefit the nextgeneration tactical aircraft Consideration is given to the followingtechnologies the forward swept wing, the thin supercritical airfoilsection, the variable incidence canard configuration to enhancesupersonic maneuvering performance, and the capability to fly toplus or minus 90 deg angle of attack and safely recover It isconcluded that the X-29 offers the opportunity for shortening theprocurement cycle and enhancing the technologies available forthe next generation tactical aircraft, this will provide to that aircraftthe potential benefits of improved transonic and supersonicefficiency, improved maneuverability and reduced approach andlanding speeds The implications of the X-29 technologies for thenext generation tactical aircraft are briefly examined B J

438


A83-36472#LARGE JET AIRCRAFT VALIDATION AND DEMONSTRATIONS- AN OVERVIEW OF BOEING EXPERIENCEJ E STEINER and L K MONTLE (Boeing Co, Seattle, WA)IN Aircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 145, 147-166(AIAA PAPER 83-1049)

Boeing experience with large jet aircraft validation anddemonstrations is examined with particular attention given to thetrend toward the use of simulation as a design and validationtool It is noted that the XB-47 integrated a new set of technology,while the X and YB-52s were used to refine details before enteringa large production program The Dash 80 vehicle was intended todemonstrate Boeing convictions to the airlines and Wright FieldThe 727 could have used a prototype but time did not permit it,while the 737 could have benefitted from more componenttechnology demonstration The first 747 was not a prototype (norwas one needed), the YC-14 mtegrated~a new set of technology,the 757 and 767 were 'prototyped' by flying them on the groundin a complex digital simulation facility It is concluded that thecircumstances were different in each case and general rules arenot feasible Future challenges are identified, including the rise inprogram costs as a justification for a more accurate technologicalknowledge B J

A83-36473#THE F-5 STORY - PROTOTYPE AND TECHNOLOGYDEMONSTRATORJ T GALLAGHER and W E FELLERS (Northrop Corp, AircraftDiv, Hawthorne, CA) IN Aircraft Prototype and TechnologyDemonstrator Symposium, Dayton, OH, March 23, 24, 1983,Proceedings New York, American Institute of Aeronautics andAstronautics, 1983, p 167-171(AIAA PAPER 83-1062)

N-156 prototype technology is examined with reference to highthrust-to-weight turbojets, remote driven engine accessories,Whitcomb theory, wing and empennage surfaces, leading edgeextensions, unimproved runways, and maintenance featuresConsideration is also given to the development of the F-5E andF-5F, the YF-17, and the F-20 B J

A83-36474#AFTI/F-16 TECHNOLOGY DEMONSTRATORM E WADDOUPS (General Dynamics Corp , Fort Worth, TX) INAircraft Prototype and Technology Demonstrator Symposium,Dayton, OH, March 23, 24,1983, Proceedings New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 173-179(AIAA PAPER 83-1059)

AFTI/F-16 is the first aircraft to begin flight testing out of aplanned AFTI series of technology demonstrators sponsored bythe Air Force Flight Dynamics Laboratory Four technology areasare being developed and integrated in the AFTI/F-16 testbeddirect force and weapon line pointing, digital flight control system,integrated flight and fire control, and pilot-vehicle interfaceadvances These are two program phases Phase I, Digital FlightControl System (DFCS), and Phase II, Automated ManeuveringAttack System (AMAS) More than 45 test flights have been carriedout in the DFCS phase to demonstrate the triplex DFCS and itsintegration into the aircraft It is noted that AMAS is beingmprepared for critical design review, and that a series ofexperiments is planned for the Phase II demonstrator to identifythe role of automation in making single-seat attack feasible B J

A83-36915#CONFIGURATION DEVELOPMENT OF A RESEARCH AIRCRAFTWITH POST-STALL MANEUVERABILITYS RANSOM (Messerschmitt-Boelkow-Blohm, VereinigteFlugtechmsche Werke GmbH, Bremen, West Germany) Journalof Aircraft (ISSN 0021-8669), vol 20, July 1983, p 599-605Research sponsored by the Bundesministerium der Verteidigungrefs

The configuration development of a small, highly maneuverableresearch aircraft is described The aircraft, of delta-canard layout,is designed specifically to investigate the subsonic unconventionalmaneuver flight envelope, which includes direct-force and post-stallflight modes Results from a low-speed wind tunnel investigationare presented, and their analysis shows that the inclusion in thelayout of twin wing-mounted forward-swept vertical tail surfacesconfers significant control and aerodynamic advantages Author

A83-36918#GENERALIZED MAXIMUM SPECIFIC RANGE PERFORMANCEE TORENBEEK and H WITTENBERG (Delft, TechnischeHogeschool, Delft, Netherlands) Journal of Aircraft (ISSN0021-8669), vol 20, July 1983, p 617-622 refs

The conditions for maximum specific range are examined for agiven aircraft/engine combination The optimum flight conditionsare derived, taking into account the effects of compressibility onthe airplane drag and the effects of engine rating, altitude, andspeed on the engine characteristics Approximations for the dragand/or engine characteristics are introduced to obtain results forspecial cases It is shown that the optimum cruise condition iseither a fixed point in the generalized drag polars (for theunconstrained case) or a combination of a fixed curve in thispolar plot with constraints on T/delta or W/delta, where T is thenet propulsive thrust, W is the aircraft all-up-weight, and delta isthe relative atmospheric pressure For turbojet and turbofan aircraftthe unconstrained and optimum cruise condition is essentiallylocated in the drag rise, and the classical criteria are not accurateenough for this class of high-subsonic aircraft It is concludedthat this method gives a useful tool for performance optimizationin the preliminary design stage, particularly if a reliable estimateof the compressibility drag is available N B

A83-36919#FLIGHT TESTS OF TOW WIRE FORCES WHILE FLYING ARACETRACK PATTERNC MATUK (Lulea, Hogskola, Lulea, Sweden) Journal of Aircraft(ISSN 0021-8669), vol 20, July 1983, p 623-627 Researchsupported by the Forsvaret Matenelverk

Airplane towing of a target with a long wire in a racetrackpattern has been investigated First the theoretical background ispresented and then the experiments are treated Twelve flightswith different airplane speeds and turn radii are studied The forceat the airplane end of the wire, and the airplane and the targetpaths are plotted The maximum force in the wire occurs after theairplane turn is finished This maximum value is due to whip effectThe occurrence of maximum and minimum values for the verticaldistance between airplane and target is demonstrated Theexperimental results are compared with theoretical results for theconditions of the experiments The overall agreement is consideredsatisfactory Therefore theoretical graphs on the maximum forcein the wire as a function of airplane speed and turn radius can beused to avoid wire failure while flying a racetrack pattern Author

A83-36921#IN-FLIGHT COMPUTATION OF HELICOPTER TRANSMISSIONFATIGUE LIFE EXPENDITUREK F FRASER (Department of Defence, Aeronautical ResearchLaboratories, Melbourne, Australia) Journal of Aircraft (ISSN0021-8669), vol 20, July 1983, p 633-640 refs


439


N83-25692*# Lockheed Corp , Burbank, CalifADVANCED MANUFACTURING DEVELOPMENT OF ACOMPOSITE EMPENNAGE COMPONENT FOR L-1011AIRCRAFT Quarterly Technical Report, 1 Jul. - 30 Sep. 197813 Oct 1978 106 p(Contract NAS1-14000)(NASA-CR-172658, MAS 1 26 172658, LR-28743, DRL-003,QTR-11) Avail NTIS HC A06/MF A01 CSCL 01C

Work continued toward the development of tooling andprocessing concepts required for a cocured hat/skin coverassembly A plan was developed and implemented to develop theprocess for using preimpregnated T300/5208 with a resin contentof 34 + or - 2 percent by weight Use of this material results in asimplified laminating process because removal by bleeding orprebleeding is no longer required The approach to this taskbasically consists of fabricating and testing flat laminated panelsand simulated structural panels to verify known processingtechniques relative to end-laminate quality The flat panels wereused to determine air bleeding arrangement and required curecycle Single and multihat-stiffened panels were fabricated usingthe established air bleeding arrangement and cure cycle with theresulting cured parts yielding excellent correlation of ply thicknesswith all surfaces clear of porosity and voids Author

N83-25693*# Lockheed Corp , Burbank, CalifADVANCED MANUFACTURING DEVELOPMENT OF ACOMPOSITE EMPENNAGE COMPONENT FOR L-1011AIRCRAFT Quarterly Technical Report, 1 Oct. - 31 Dec. 197822 Jan 1979 82 p(Contract NAS1-14000)(NASA-CR-172659, NAS 1 26172659, LR-28843, DRL-003,QTR-12) Avail NTIS HC A05/MF A01 CSCL 01C

Work on process verification and tooling developmentcontinued The cover process development was completed withthe decision to proceed with low resin content prepreg material(34 + or - 3% by weight) in the fabrication of production readinessverification test (PRVT) specimens and the full-scale covers Thestructural integrity of the cover/joint design was verified with thesuccessful test of the cover attachment to fuselage ancillary testspecimen (H25) Failure occurred, as predicted, in the skin panelaway from the fuselage joint at 141 percent of the design ultimateload With the successful completion of the H25 test, the PRVTcover specimens, which are identical to the H25 ancillary testspecimen, were cleared for production Eight of the twenty coverspecimens were fabricated and are in preparation for test Alltwenty of the PRVT spar specimens were fabricated and alsowere prepared for test The environmental chambers used in thedurability test of ten cover and ten spar PRVT specimens werecompleted and installed in the load reaction frames Author

N83-25694*# Lockheed Corp , Burbank, CalifADVANCED MANUFACTURING DEVELOPMENT OF ACOMPOSITE EMPENNAGE COMPONENT FOR L-1011AIRCRAFT Quarterly Technical Report, 1 Jan. 1979 - 31 Mar.197920 May 1979 98 p(Contract NAS1-14000)(NASA-CR-172657, NAS 1 26 172657, QTR-13, LR-29058,DRL-003) Avail NTIS HC A05/MF A01 CSCL 01C

Work in process verification and tooling development continuedThe decision was made to redesign the ribs to a more producibledesign The bead was eliminated and the truss ribs changed toplain C sections The solid web rib stiffeners were eliminated aswell as the beads and the webs are now reinforced with a syntacticcore Syntectic is an epoxy containing glass microballoons Twocover specimens were successfully tested The first specimen (H27)was designed to verify the stability and compression strength ofthe cover when it is hot and wet Failure occurred at 120 percentof design ultimate load As the failure appeared to be fixture inducedand was limited to one end of the panel, the remainder of thepanel will be tested The second specimen (H28) was designedto verify the failsafe aspects of the design The test verified thedesign Preparation of the PRVT test facility is nearmg completion

and all ten spar durability specimens were installed in the testchambers S L

N83-25695*# Textron Bell Helicopter, Fort Worth, TexCORRELATION AND EVALUATION OF INPLANE STABILITYCHARACTERISTICS FOR AN ADVANCED BEARINGLESS MAINROTOR Final ReportW H WELLER May 1983 85 p refs(Contract NAS2-11269)(NASA-CR-166448, NAS 1 26 166448) Avail NTIS HC A05/MFA01 CSCL 01C

A program of experimental and analytical research wasperformed to demonstrate the degree of correlation achievedbetween measured and computed rotor inplane stabilitycharacteristics The experimental data were obtained from hoverand wind tunnel tests of a scaled bearmgless main rotor modelBoth isolated rotor and free-hub conditions were tested Testparameters included blade built-in cone and sweep angles, rotorinplane structural stiffness and damping, pitch link stiffness andlocation, and fuselage damping, inertia, and natural frequencyAnalytical results for many test conditions were obtained Inaddition, the analytical and experimental results were examined toascertain the effects of the test parameters on rotor ground andair resonance stability The results from this program are presentedherein in tabular and graphical form Author

N83-25696# Air Force Flight Dynamics Lab, Wright-PattersonAFB, OhioAIRCRAFT EQUIPMENT RANDOM VIBRATION TEST CRITERIABASED ON VIBRATIONS INDUCED BY TURBULENT AIRFLOWACROSS AIRCRAFT EXTERNAL SURFACESJ F DREHER 1983 13 p refs(AD-A123281) Avail NTIS HC A02/MF A01 CSCL 01C

Vibrations within jet aircraft are caused by a number ofphenomena The principal sources, generally are jet engine noiseand turbulent airflow (pseudo-noise) which impinge on aircraftexternal surfaces, gust, landing, and takeoff loads, and on-boardmechanical equipment such as engines and pumps This paperdescribes the structural vibrations induced by turbulent airflow andgeneralizes the findings to develop pertinent, adaptable randomvibration test criteria for aircraft equipment These criteria are thoserecently proposed for inclusion in Method 514 of MIL-STD-810C,Environmental Test Methods Author (GRA)

N83-25697# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringEXPERIMENTAL TESTING OF FLYING QUALITIES THEORIESM.S. ThesisN H KRYS Dec 1982 263 p refs(AD-A124699, AFIT/GE/EE/82D-43) Avail NTIS HC A12/MFA01 CSCL 14B

An analog computer simulation was used to model the rolldynamics of the generic aircraft which had been evaluated on thevariable stability NT-33A aircraft Sum of sine waves and randomstep functions were used as the two different command signalsThe purpose of this study was to determine what effect the natureof the command signal had on the pilot rating of the tasksimulation Author (GRA)

N83-25698# Army Aviation Engineering Flight Activity, EdwardsAFB, CalifCLIMATIC LABORATORY SURVEY HUGHES YAH-64HELICOPTER Final Report, 2 Nov. • 16 Dec. 1981G L BENDER, C F ADAM, and R T SAVAGE Mar 1982260 p refs(AD-A124670, USAAEFA-80-07) Avail NTIS HC A12/MF A01CSCL 01C

Environmental testing of the YAH-64 helicopter was conductedin the McKmley Climatic Laboratory, Eglm Air Force Base, FloridaThe US Army Aviation Engineering Flight Activity was responsiblefor the evaluation of aircraft systems and the US Army AviationDevelopment Test Activity was responsible for the missionequipment evaluation The test consisted of 144 hours of aircraft

440


operating time between 2 November and 16 December 1981Testing was accomplished at 125, 70, -25, and -50 F with theaircraft attached to the hangar floor At each temperature, testingconsisted of preflight inspections, APU and engine starts, simulatedmission profiles, engine shut down, and maintenance inspectionsNine deficiencies were found which would preclude missionaccomplishment (1) the fire control computer was unreliable, (2)the symbol generator required an excessive warm-up time at coldtemperatures, (3) the heading and attitude reference system wasunreliable, (4) the environmental control unit failed to provideadequate heating or cooling to the cockpit and avionics bays at-25 F, -50 F, and 125 F, (5) the TADS/PNVS and weapons systemsdid not function adequately at 125 F, (6) the APU aborted itsstart sequence because it could not accelerate the accessorygearbox to operating speed at -25 F and -50 F, (7) the hydraulichand pump was ineffective at -25 F and -50 F, (8) the utilityhydraulic manifold allowed the accumulator to bleed off at -25 Fand -50 F, and (9) failure of the hydraulic flex lines at cold ambienttemperatures GRA

N83-25699# Computational Mechanics Consultants, Knoxville,TennAN ASSESSMENT OF FACTORS AFFECTING PREDICTION OFNEAR-FIELD DEVELOPMENT OF A SUBSONIC VSTOL JET INCROSS-FLOW Final Report, Sep. 1981 - Jun 1982A J BAKER and J A ORZECHOWSKI Warminster, PaNADC Jun 1982 41 p refs(Contract N62269-81-C-0395)(AD-A124583, NADC-81177-60) Avail NTIS HC A03/MF A01CSCL 01C

A three-dimensional parabolic Navier-Stokes numerical solutionalgorithm has been analyzed for prediction of the nearfield flowdevelopment of a VSTOL jet in subsonic crossflow The essentialaspects of algorithm definition, with regards to initial and boundarycondition specifications, has been summarized A momentumconserving pressure gradient computation has been developed tocomplete the problem definition and facilitate problem initializationA sequence of overlapping interaction solutions has been evaluatedfor prediction of a circular jet at gamma = 80 The results of the3DPNS predictions shave compared qualitatively with the sparseavailable experimental data It is crucial that quality data be acquiredto permit quantitative assessment of the results of this analysisprocedure Author (GRA)

N83-25700# Bihrle Applied Research, Inc , Jericho, N YF-14 ROTARY BALANCE TESTS FOR AN ANGLE-OF-ATTACKRANGE OF 0 DEG TO 90 DEC Final ReportB BARNHART Warminster, Pa NADC Jan 1983 24 p(Contract N62269-82-C-0233, WF41400000)(AD-A124468, NADC-81293-60) Avail NTIS HC A02/MF A01CSCL 148

A 1 /12-scale model of the F-14 was tested on the rotary balancelocated in the Langley Spin Tunnel Data were obtained for thebasic airplane in the maneuver configuration with various controlsettings at three wing sweeps The data were supplied to theNaval Air Development Center on magnetic tape This reportpresents a description of these tests and the information suppliedon the data tape, as well as a list of spin modes predicted for theF-14 utilizing the rotary balance data Author (GRA)

N83-25701# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringAN EXPERIMENTAL/ANALYTICAL INVESTIGATION INTO THEPERFORMANCE OF A 20-PERCENT THICK, 8.5-PERCENTCAMBERED, CIRCULATION CONTROLLED AIRFOIL M.S.ThesisJ K HARVELL Dec 1982 84 p refs(AD-A124732, AFIT/GAE/AA/82D-13) Avail NTIS HC A05/MFA01 CSCL 01C

This study was conducted to investigate the effect of twotangentially blown slots on the performance of a 20-percent thick,8 5-percent cambered elliptical airfoil Lift, drag, and momentcoefficients were obtained at a test Reynolds number of 9 5 x

100,000 for secondary slot locations of 73 5 and 83 5 deg Resultsshow that the use of two tangentially blown slots enables thegeneration of higher lift coefficients at lower blowing rates Thisfeature enables the test airfoil to equal the performance of singleslotted blown airfoils at lower blowing rates therefore reducingthe parasitic losses and resulting in higher lift/drag ratios A limitedstudy of the ability of the (TRACON) program to predict circulationcontrolled airfoil performance was conducted The program failedto provide accurate predictions for the pressure distribution orforce coefficients for the airfoil configuration of this study Thisstudy also found that using different geometry smoothingtechniques in the region of the slot resulted in large variations inTRACON's performance predictions GRA

N83-25702# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringDESIGN AND ANALYSIS OF A SUBCRITICAL AIRFOIL FORHIGH ALTITUDE, LONG ENDURANCE MISSIONS M.S. ThesisI AHMAD Dec 1982 132 p refs(AD-A124757, AFIT/GAE/AA/82D-1) Avail NTIS HC A07/MFA01 CSCL 01C

An airfoil was designed using the 'inverse design' method Theairfoil was tailored to meet the requirements of high altitude, longendurance missions The cruise Mach number was 0 65 socompressibility effects were included In the procedure used, abasic airfoil was generated to meet the thickness and momentrequirements It was then refined to ensure desired behavior ofthe boundary layer at the operating angles of attack Computercodes designed by Richard Eppler were used for this study Theairfoil was analyzed by using a viscous effects analysis programdesigned by Shang et al and a comparison was made with resultsobtained through Eppler's code GRA

N83-25703# Aeronautical Research Labs, Melbourne(Australia)RESONANCE TESTS ON THE TAIL OF A CT4 AIRCRAFTA GOLDMAN Sep 1982 27 p(AD-A124566, ARL/STRUC-TM-345) Avail NTIS HC A03/MFA01 CSCL 01C

A resonance test has been carried out on the tail section of aCT4 aircraft Natural modes and frequencies of the tailplane weremeasured and these results are presented Author (GRA)

N83-25704# Systems Technology, Inc , Hawthorne, CalifPROPOSED MIL STANDARD AND HANDBOOK: FLYINGQUALITIES OF AIR VEHICLES. VOLUME 2 PROPOSED MILHANDBOOK Final Report, Apr. 1980 - Jul. 1982R H HOH, D G MITCHELL, I L ASHKENAS, R H KLEIN, RK HEFFLEY, and J HIDGKINSON (McDonnell Aircraft Co)Wright-Patterson AFB, Ohio AFWAL Nov 1982 899 p refs(Contract F33615-80-C-3604, AF PROJ 2403)(AD-A123726, AFWAL-TR-82-3081-VOL-2) Avail NTIS HCA99/MF A01 CSCL 01C

MIL-F-8785C, Military Specification -- Flying Qualities of PilotedAirplanes, has been reformatted into a MIL Standard and asupporting MIL Handbook This report is a draft of the proposedMIL Standard, which has been developed by Systems Technology,Inc, with the McDonnell Aircraft Company acting in a consultingrole It is presented to industry and the United States armed forcesfor comments and proposed revisions The responsibility for thelegal MIL Standard and Handbook rests within the armed forcesThis draft will be considered and form the basis for revisions,industry and government comments and a tn-service review inthe process of developing the MIL Standard and HandbookSuggested values and background information are contained inthis volume MIL-F-8785C and the backup documents to both itand its predecessor, MIL-F-8785B, were reviewed extensivelyMuch of the material contained therein is still considered to bevalid and relevant and has been retained in this document

Author (GRA)

441


N83-25705# Army Aviation Engineering Flight Activity, EdwardsAFB, Calif Directorate for Development and QualificationAIRWORTHINESS AND FLIGHT CHARACTERISTICS TEST.PART 2. YAH-64 ADVANCED ATTACK HELICOPTER FinalReport, 8-17 Dec. 1981B D PICASSO, III, G T DOWNS, R M BUCKANIN, and J DOTTOMEYER Feb 1982 152 p refs(AD-A125270, USAAEFA-80-17-2) Avail NTIS HC A08/MF A01CSCL 01C

The Airworthiness and Flight Characteristics (A&FC) EvaluationPart 2, of the prototype YAH-64 helicopter (S/N 77-23258) wasconducted at Palomar Airport, Carlsbad, California (elevation 328ft) A total of 12 flights were conducted between 8 December and17 December 1981 and 143 productive hours were flown Priorto this test significant design changes were incorporated in theflight control system, the digital automatic stabilization equipment(DASE) and the stabilator system to correct objectionablecharacteristics determined during the airworthiness qualificationprogram Significant improvements in handling qualities were notedsince the previous evaluation Uncommanded control inputs,caused by recentenng of the SAS actuators, upon failure ordisengagement of the DASE may cause a potentially hazardoussituation The instrument flight characteristics of the YAH-64 aresatisfactory in smooth air but have yet to be evaluated in turbulentconditions Manual programming of the stabilator in rearward flightdid not significantly reduce objectional vibration at the pilot's stationResults of this test have shown that both previously reporteddeficiencies and 14 shortcomings have been corrected Onedeficiency not previously observed, was identified the possibilityof a false indication of dual engine failure following a single enginefailure Two previously unreported shortcomings were alsoidentified GRA

N83-25706# European Space Agency, Pans (France)EVALUATION OF AERODYNAMIC DERIVATIVES FROMDO-28-TNT FREE-FLIGHT MODEL TESTSM MARCHAND Apr 1983 40 p refs Transl into ENGLISHof "Bestimmung der Denvate ernes Do-28-TNT Modells ausFreiflugversuchen', DFVLR, Brunswick Report DFVLR-FB-82-17,May 1982 Original report in GERMAN previously announced asN83-18711(ESA-TT-784, DFVLR-FB-82-17) Avail NTIS HC A03/MF A01,original German version available from DFVLR, Cologne DM1650

Free flight tests were conducted on a Do-28-TNT model todetermine the derivatives of longitudinal motion Preprogrammedcontrol inputs were given to the elevator or the flaps during thefree flight phase The mathematical model which included thefrequency dependent effects of rapid flap deflection and the pitchrate measuring system is described Analysis reveals that thedynamics of the measuring circuitry must be considered in themathematical model Changes in the resulting derivatives if thetime constant of a filter located in the pitch rate channel was notknown exactly, or was neglected were examined In order todetermine pitching moment derivatives, a fast combined step inputsignal is best For the normal force derivatives a slower input withadditional trimming by mass changes is preferable Comparison ofthe identifications performed with different mathematical modelsshows that for an investigation into the influence of nonstationaryeffects a significantly higher frequency excitation, in the range of5 to 10 Hz, is necessary Author (ESA)

N83-26812# Air Force Flight Dynamics Lab, Wright-PattersonAFB, OhioSTATISTICAL EXPERIMENTAL DESIGNS IN COMPUTER AIDEDOPTIMAL AIRCRAFT DESIGN Final ReportK S NAGARAJA and R B RAM (State Univ of New York) InAFWAL A Collection of Papers in the Aerospace Sci p 648-670Jun 1982 refsAvail NTIS HC A99/MF A01 CSCL 01C

A review of the statistical experimental designs which arerelevant to the selection process of the design variables is madeAlthough several aerospace industries still use Latin Square

techniques, the inherent shortcomings of the approach are notrecognized Optimal aircraft designs which are derived from sucha deficient method become suspect, and reliability and cost savingcan both become unattainable An alternate approach, calledD-optimal design, which has several advantages due to its reliabilityand efficiency, is discussed R J F

N83-26829*# Lightning Technologies, Inc, Pittsfield, MassAIRCRAFT LIGHTNING-INDUCED VOLTAGE TEST TECHNIQUEDEVELOPMENTS Final ReportK E CROUCH Jun 1983 71 p refs(Contract NAS4-2930)(NASA-CR-170403, NAS 1 26 170403, LT-82-132) Avail NTISHC A04/MF A01 CSCL 01C

High voltage safety, fuels safety, simulation, andresponse/measurement techniques are discussed Travelling wavetransit times, return circuit conductor configurations, LC laddernetwork generators, and repetitive pulse techniques are alsodiscussed Differential conductive coaxial cable, analog fiber opticlink, repetitive pulse sampled data instrumentation system, flashA/D optic link system, and an FM telemetry system areconsidered Author

N83-26830# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringDYNAMIC CHARACTERISTICS OF AERIAL REFUELINGSYSTEMS M.S. ThesisT J CARTER, III Dec 1982 91 p refs(AD-A124770, AFIT/GAE/AA/82D-4) Avail NTIS HC A05/MFA01 CSCL 01B

Two aircraft refueling system configurations were simulatedusing HYTRAN, an existing transient flow analysis computerprogram Transient pressure response subsequent to downstreamvalve closure was investigated for the KC-135 and a laboratorytest rig and compared to available experimental data and previousresearch Parametric studies were performed of system variablesvalve closure time, valve area versus time (closure curves), andvariation in surge attenuation components (surge boot,accumulators) A typical closure curve for quick disconnects wasapproximated and verified The simulation results comparedfavorably with experimental data and previous work Transientpressure was found to be sensitive to accumulator or surge bootprecharge pressure while changes in accumulator volume had littleeffect Variations in accumulator entry line diameter or lengthaffected transient pressure and settling time Increased valvesnubbing reduced maximum transient pressures Author (GRA)

N83-26831*# Boeing Commercial Airplane Co , Seattle, WashSELECTED ADVANCED AERODYNAMICS AND ACTIVECONTROLS TECHNOLOGY CONCEPTS DEVELOPMENT ON ADERIVATIVE B-747 AIRCRAFT Summary Report, May 1977 -May 1979NASA Washington Jun 1983 51 p refs(Contract NAS1-14741)(NASA-CR-3295, NAS 1 26 3295) Avail NTIS HC A04/MF A01CSCL 01C

Analytical design and wind tunnel test evaluations coveringthe feasibility of applying wing tip extensions, wmglets, and activecontrol wing had alleviation to the model B747 are describedAerodynamic improvement offered by wing tip extension and wmgletindividually, and the combined aerodynamic and weightimprovements when wing load alleviation is combined with the tipextension or the wmglet are evaluated Results are presented inthe form of incremental effects on weight mission range, fuel usage,cost, and airline operating economics Author

442

06 AIRCRAFT INSTRUMENTATION

N83-26832# Air Force Wright Aeronautical Labs,Wright-Patterson AFB, Ohio Mechanical BranchEXPERIMENTAL ANALYSIS OF THE PERFORMANCE OF ANANNULAR PERIPHERAL JET VEHICLE IN GROUND EFFECTFinal Report, Aug. 1980 - Jan. 1982R J ALMASSY Oct 1982 42 p refs(Contract AF PROJ 2402)(AD-A124949, AFWAL-TR-82-3043) Avail NTIS HC A03/MFA01 CSCL01C

Two annular peripheral jet air cushion models were designed,fabricated and tested in-house at the Mobility DevelopmentLaboratory (AFWAL/FIEMB) at Wright-Patterson AFB, OH Thevehicles were designed to attain maximum hover height at a fixedlevel of available power based on Barrart Theory, and achievemaximum static hover stability The assumptions and analyticdevelopment of Barratt Theory are discussed, as well as somedesign aspects to achieve vehicle cushionborn stability Test resultsindicated Barratt lift predictions to be slightly conservative Bothvehicles were unstable at high hover power heights in their basicconfigurations The addition of several configurations of verticalstrakes compartmenting the cushion area achieved varyingimprovements to vehicle stability The addition of full cushion depthcruciform strakes completely stabilized the vehicles Vehicleinstability was concluded to be caused by aerodynamic activity inthe cushion area induced by shear from high momentum jetairflow GRA

N83-26833# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringSURVIVABILITY OF INTERDICTION AIRCRAFT: SENSITIVITYTO TERRAIN FOLLOWING, COMMAND ALTITUDE, VELOCITYAND ELECTRONIC COUNTER MEASURES M.S. ThesisM D REID Dec 1982 230 p refs(AD-A124870, AFIT/GOR/MA/82D-2) Avail NTISHCA11/MFA01 CSCL 01C

The FORTRAN program TERRAIN is a deterministic model ofa tactical aircraft penetrating a Surface-to-Air (SAM) andAnti-Aircraft Artillery (AAA) threat TERRAIN generates a terrainfollowing flight path profile based on specified flight parametersand then assesses the aircraft vulnerability in terms of exposuretime and shots taken by individual threat site and the total defenseModifications were made to assess aircraft survivabihty (theprobability of kill of the aircraft) and to calculate the effect on theprobability of kill of electronic countermeasures The TERRAINmodel is particularly sensitive to the selection of beddown, rate offire for AAA, aircraft velocity, and aircraft commanded clearancealtitude A comparison of the strengths and weaknesses of theoriginal TERRAIN model, the modified TERRAIN model, and sixother SAM/AAA models has been compiled A user's guide forthe modified TERRAIN model is provided Author (GRA)

N83-26835# Calspan Corp, Buffalo, N Y Flight ResearchDeptLATERAL FLYING QUALITIES OF HIGHLY AUGMENTEDFIGHTER AIRCRAFT, VOLUME 1 Final Report, Mar. 1980 - May1982S J MONAGAN, R E SMITH, and R E BAILEY Wright-PattersonAFB, Ohio AFWAL Jun 1982 85 p refs(Contract F33615-79-C-3618)(AD-A118070, CALSPAN-6645-F-8-VOL-1,AFWAL-TR-81-3171-VOL-1) Avail NTIS HC A05/MF A01CSCL 01C

This in-flight simulation experiment, using the USAF NT-33variable stability aircraft operated by Calspan, was undertaken togenerate lateral-directional flying qualities data applicable to highlyaugmented fighter aircraft In particular, the effects of time delayand prefilter lag in the lateral flight control system were studiedfor representative Flight Phase Category A and C tasks Thecombined effects of those elements as well as the effects ofnonlinear command gam and high Dutch roll damping were alsoevaluated Tasks included were actual target tracking, air refuelingand precision landing as well as special Head-Up Display (HUD)tracking tasks Results indicated that a properly designed HUDbank angle tracking task is a valid flying qualities evaluation taskData show that lateral flying qualities are very sensitive to controlsystem time delay and very short values of roll mode time constanttypically result in poor lateral flying qualities Excellent separationof the data into flying qualities level is achieved for the CategoryA task data using time domain equivalent indicated by the data,sensitivity to equivalent time delay is a minimum at this valueVolume I contains the body of the report, while Volume II consistsof the Appendices GRA

N83-26836# Research Inst of National Defence, Linkoeping(Sweden)SIMULATION PROGRAM OF ROTARY WINGS [PROGRAMFOER SIMULERING AV HELIKOPTERROTOR]A WALLIN Dec 1982 31 p In SWEDISH(FOA-C-30308-E1) Avail NTIS HC A03/MF A01

A computerized simulation program written in FORTRAN forproducing images of rotary wings by means of an image-generatinginfrared camera is described The rotor image can be completedby adding a function representing the helicopter body Correlativenoise, subdivided in rectangles, can be added to the image

Author (ESA)

06

AIRCRAFT INSTRUMENTATION

Includes cockpit and cabin display devices, and flight instruments

N83-26834# Naval Air Development Center, Warmmster, PaAircraft and Crew Systems Technology DirectorateSTATISTICAL REVIEW OF COUNTING ACCELEROMETERDATA FOR NAVY AND MARINE FLEET AIRCRAFT SemiannualSummary Report, 1 Jan. 1962 - 30 Jun. 1982W J WILLIAMS 1 Nov 1982 158 p(AD-A124966, NADC-13920-2) Avail NTIS HC A08/MF A01CSCL 01A

This is a semiannual progress report, and it presents aspecialized summary of the data in the counting accelerometerprogram Statistics describing Navy and Marine aircraft cumulativeg-count exceedances are calculated and tabulated Thesetabulations are separated by calendar time and into four majorcategories of Fleet experience Navy Training, Navy Combat, MarineTraining, and Marine Combat Load rate distributions in countsper 1000 hours are calculated for all g-levels Distribution statistics(mean, standard deviation, and skewness) are presented for mostmodels GRA

A83-36207#ADVANCED DISPLAY TECHNIQUES FOR TRAINING THEMULTI-MEMBER TACTICAL AIR CREWG ALBERS (General Electric Co , Simulation and Control SystemsDept, Daytona Beach, FL) IN Flight Simulation TechnologiesConference, Niagara Falls, NY, June 13-15, 1983, Collection ofTechnical Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 32-34(AIAA PAPER 83-1079)

The C-130 Weapon System Trainer Visual System developedfor the Military Airlift Command at Little Rock AFB is describedThe 6-wmdow, 10-window-position visual display system, drivenby five 875-line, 1000 pixel/line CIG channels, is shown to meetthe requirements for multimember-crew training field of view (from30 x 40 to 36 x 48 deg), visual-cue content, environmental context,correlation with navigational aids, radar, and station-keepingdevices, textural relief, resolution (better than 2 7 arc mm),data-base geographic and logistic size (over 33,000 sq n mi),realistic night operation, night-vision goggle compatibility, and cost

443

06 AIRCRAFT INSTRUMENTATION

effectiveness The solution of the problems associated with theCRT reproduction of night conditions is given specialconsideration T K

A83-36303#MODERN TECHNOLOGY AND AIRBORNE ENGINE VIBRATIONMONITORING SYSTEMSD J RAY (Endevco, San Juan Capistrano, CA) and R L KALLIO(Boeing Commercial Airplane Co, Seattle, WA) AIAA, SAE, andASME, Joint Propulsion Conference, 19th, Seattle, WA, June 27-29,1983 6 p(AIAA PAPER 83-1240)

An improved technique for measuring in-flight turbine enginevibration levels is described It is noted that the normally-usedvelocity coils are subject to wear and are orientation-dependentNewer aircraft are being equipped with piezoelectricaccelerometers, which feature high impedance levels but aresubject to high electrical noise levels The introduction of a digitaltracking filter into digital signal processing avionics has permittedtracking the rotor speed with a microcomputer by using anarrowband response Noise is thereby eliminated, and the deviceshave been implemented in the engines on the 747, 757, and 767aircraft The microprocessor can be programmed to receive multiplechannels of tachometer data, as well as to hold preset vibrationalarm levels that will lead to indication appearing on the flightdeck when reached M S K

A83-36325*ADVANCED TECHNIQUES FOR GAS AND METALTEMPERATURE MEASUREMENTS IN GAS TURBINE ENGINESE A PINSLEY (United Technologies Corp, Pratt and WhitneyGroup, West Palm Beach, FL) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 9 prefs(AIAA PAPER 83-1291)

In connection with a continuing improvement regarding theperformance of new gas turbine designs, both gas and metaltemperature measurements for the next generation of engines willhave to be performed at increasingly higher temperature levels inregions where heat fluxes, g-loads, erosion rates, and sensitivityof measurement requirements to instrument installationperturbations will all increase The present investigation isconcerned with the status of a number of advanced techniquesfor high temperature measurement currently in various stages ofdevelopment and acceptance The devices considered for themeasurement of metal temperatures include thin filmthermocouples, pyrometers, and IR scanning cameras Approachesfor determining gas temperatures are also discussed, taking intoaccount Coherent Anti-Stokes Raman spectroscopy (CARS) anddynamic temperature sensors G R

A83-36326#APPLICATION OF THIN FILM STRAIN GAGES ANDTHERMOCOUPLES FOR MEASUREMENT ON AIRCRAFTENGINE PARTSW R STOWELL and R A WEISE (General Electric Co , Cincinnati,OH) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 6 p(AIAA PAPER 83-1292)

In connection with aerodynamic disturbances caused by wirestrain gages on compressor blade air foils, a program was initiatedto develop mesurement techniques which could provide dynamicstrain information from blades in an operating test engine withoutaffecting the response of the blades to their environment andwithout changing significantly the airflow Reliable gages could bedeveloped for measurements at temperatures up to 1000 F (540C) Attention is given to the development of gages which arereliable at metal temperatures of 1200 F (approximately 650 C)Reliable thermocouples for measurements on operating turbinebuckets are also being developed It is intended to apply thin filmthermocouples to turbine buckets in connection with a studyinvolving the mapping of temperature profiles in the vicinity of aircooling holes on advanced bucket designs Attention is given to a

thin film insulator, quality control, and aspects of thin filmthermocouple development G R

A83-36327#INSTRUMENTAL PROBLEMS IN SMALL GAS TURBINEENGINESJ ALLAN, III (Garrett Turbine Engine Co, Phoenix, AZ) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 12 p(AIAA PAPER 83-1293)

The small size, high rotational speeds, and unusual flowpathconfigurations associated with small gas turbine enginedevelopment programs make it necessary to developinstrumentation techniques and systems compatible with the specialproblems encountered in connection with the smaller enginesTypical measurement techniques include blade tip clearancemeasurement systems, slip-ring systems, telemetry systems, andtorque measurement systems A description is provided of the'single-point probe' survey system This system represents acomputer-controlled preprogrammed traversing actuator and dataacquisition system which allows vane wake mapping and rotorperformance mapping without the use of traditional wake rakesThis method of performance mapping reduces flow blockage andflow disturbances and eliminates measurement inaccuraciesassociated with sensor-to-sensor variations G R

A83-36613A TRUE AIR SPEED SENSOR FOR MINIATURE UNMANNEDAIRCRAFTJ A C BEATTIE (Royal Aircraft Establishment, Farnborough,Hants, England) Aeronautical Journal (ISSN 0001-9240), vol87, May 1983, p 173-175 refs

A prototype sensor with digital output is described Vortexshedding principles are exploited by using a bluff body withend-plates to produce a stable set of vortices alternately from theedges of the body Vortex production frequency is directlyproportional to the speed of the fluid past the body A pair ofprinted thick film thermistors detect the vortices Tests showexcellent linearity of response, although sensor geometry, andsignal processing electronics can be improved Previouslyannounced in STAR as N82-14086 Author

N83-25707*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaDESCRIPTION OF THE COMPUTATIONS AND PILOTPROCEDURES FOR PLANNING FUEL-CONSERVATIVEDESCENTS WITH A SMALL PROGRAMMABLE CALCULATORD D VICROYandC E KNOX May 1983 37 p refs(NASA-TM-85642, NAS 1 1585642) Avail NTIS HC A03/MFA01 CSCL01D

A simplified flight management descent algorithm wasdeveloped and programmed on a small programmable calculatorIt was designed to aid the pilot in planning and executing a fuelconservative descent to arrive at a metering fix at a time designatedby the air traffic control system The algorithm may also be usedfor planning fuel conservative descents when time is not aconsideration The descent path was calculated for a constantMach/airspeed schedule from linear approximations of airplaneperformance with considerations given for gross weight, wind, andnonstandard temperature effects The flight management descentalgorithm and the vertical performance modeling required for theDC-10 airplane is described Author

N83-25709# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringMODELING THE HELMET-MOUNTED SIGHT SYSTEM M.S.ThesisW R CLUBINE Dec 1982 201 p refs(AD-A124681, AFIT/GE/EE/82D-24) Avail NTIS HC A10/MFA01 CSCL 17G

This report describes the development of an error model forthe Helmet-Mounted Sight System This model is designed togenerate the HMS aiming errors that are encountered when the

444

07 AIRCRAFT PROPULSION AND POWER

sight is used in the Navigation Update role This report details theresearch performed to identify, catagonze, and model theHelmet-Mounted Sight (HMS) errors The HMS error model includeserror generated by the human operator, the HMS equipment, thevibration environment, canopy refraction, and the systemboresightmg procedure The final portion of this reportdemonstrates the performance of this model in a Monte Carlosimulation program Author (GRA)

N83-25710# Defence and Civil Inst of Environmental Medicine,Downsview (Ontario)THEORY UNDERLYING THE PERIPHERAL VISION HORIZONDEVICEK E MONEY Dec 1982 13 p refs(AD-A124426, DCIEM-TC-82-C-57) Avail NTIS HC A02/MFA01 CSCL 01D

A simple statement of the Peripheral Vision Horizon Device(PVHD) theory is that the likelihood of pilot disonentation in flightcan be much reduced by providing a new kind of artificial horizonthat will provide orientation information to peripheral vision Inconsidering the validity of this theory, three questions which arecrucial are discussed (1) Why was the artificial horizon chosen,instead of some other flight instrument' (2) Why is peripheralvision used instead of foveal vision' (3) Is there convincingevidence that peripheral vision is particularly well suited to theprocessing of orientation information' GRA

07

AIRCRAFT PROPULSION AND POWER

Includes prime propulsion systems and systems components, e g ,gas turbine engines and compressors, and on-board auxiliary powerplants for aircraft

A83-34253THERMAL CYCLING IN COMPACT PLATE-FIN HEATEXCHANGERST D EASTOP and G SINGH (Wolverhampton Polytechnic,Wolverhampton, England) IN Numerical methods in thermalproblems Volume 2 Proceedings of the Second InternationalConference, Venice, Italy, July 7-10, 1981 Swansea, Wales,Pmendge Press, 1981, p 723-736 refs

Compact plate-fin heat exchangers of the considered type areused in the aircraft industry because of their small volume andweight The heat exchanger consists of a series of flat plates,sandwiching corrugated plates, and separated by spacer bars Theheat exchanger considered in the present investigation is subjectedto a sudden flow of hot air on one side of the exchanger with theair coolant side inlet temperature remaining constant Since thissudden increase in temperature occurs every time the aircraft takesoff, the heat exchanger is subjected to a thermal cycle with along time period A cross-flow plate-fin type heat exchanger withboth fluids unmixed is analyzed numerically, taking into accountthe thermal storage of the fluids and the metal, but assuming thatthe fluid properties are constant G R

A83-35039THE USE OF A STRUCTURAL MODEL FOR DETERMINING THEADAPTABILITY CURVE FOR TURBINE DISKS IN STRESSCONCENTRATION ZONES [ISPOL'ZOVANIE STRUKTURNOIMODELI DLIA OPREDELENIIA KRIVOI PRISPOSOBLIAEMOSTITURBINNYKH DISKOV V ZONAKH KONTSENTRATSIINAPRIAZHENII]A E GINZBURG and E T KULCHIKHIN Problemy Prochnosti(ISSN 0556-171X), May 1983, p 38-40 In Russian refs

A method based on the adaptability theory is proposed for theanalysis of turbine disks in the case where alternating-sign inelasticdeformation occurs in the stress concentration zone Here, a curvecalculated on the basis of a structural model for an

elastoviscoplastic medium is used instead of the experimentallydetermined cyclic deformation curve The method can be usedfor the stress-strain analysis of gas-turbine disks loaded inaccordance with a complex program (e g, cyclic loading withholds) V L

A83-35675AR.318 - ITALY'S LOW-COST GA TURBOPROPJ MOXON Flight International (ISSN 0015-3710), vol 123, May21, 1983, p 1398, 1399

Design and performance features of the AR318 600 shpturboprop, targeted for production in 1985, are detailed TheAR318, the first turbine engine to be wholly built in Italy, hasbeen designed for simplicity and low-cost manufacture It has asingle shaft, a single-stage centrifugal compressor at one enddriven by a two-stage turbine at the other, and a reverse flowannular combustion chamber An epicychc gearbox transfers powerto the propeller, and drives the oil pump, fuel control unit, thestarter/generator, and the propeller control unit The dry weight is310 Ib and fuel consumption is 0578 Ib/hr per shp Furtherincreases of power to 850 shp are projected with a new centrifugalcompressor There is no provision for turbine blade coolingOverhaul life is expected to be 500 hr at first, and 3500 hr withexperience M S K

A83-35790TEMPERATURE AND COMPOSITION MEASUREMENTS IN ARESEARCH GAS TURBINE COMBUSTION CHAMBERW P JONES and H TORAL (Imperial College of Science andTechnology, London, England) Combustion Science andTechnology (ISSN 0010-2202), vol 31, no 5-6, 1983, p 249-275Research sponsored by Rolls-Royce, Ltd refs

Motivation regarding an improvement in the design of gasturbine combustion chambers is related to the need to achieveimproved combustor exit temperature profiles, longer combustorlife, and reduced combustion generated pollutant emission levelsBetter understanding of combustor operation is required to achievethese objectives and this in turn requires sufficiently detailedexperimental data The present investigation is concerned withmeasurements in a model can-type combustion chamber intendedto be representative of aircraft gas turbine combustors The fuelemployed was gaseous propane Measurements are presented ofO2, CO, C02, H2, unburnt hydrocarbons, NOx, and temperature,taking into account the exit plane and various planes within thecombustor at different air inlet temperatures G R

A83-35801INTERNATIONAL SYMPOSIUM ON AIR BREATHING ENGINES,6TH, PARIS, FRANCE, JUNE 6-10, 1983, SYMPOSIUM PAPERSF S BILLIG, ED (Johns Hopkins University, Laurel, MD) NewYork, American Institute of Aeronautics and Astronautics, 1983,733 p

Among the topics discussed in the present conference onairbreathing aircraft and missile propulsion systems are solidpropellant ramjets, combustion instability in liquid-fueled ramjets,gas turbine engine combustion research trends, the effects of air,liquid and injector geometry variables on the performance of aplain jet airblast atomizer, the prediction of spray evaporation rates,the internal and external transonic flow fields of inlets, the localizedstability of vortices, the lean extinction limit for pilot flame holders,and turbulent flame propagation in swirl-stabilized flames Alsoconsidered are boundary layer development in a supersonic intake,computational techniques for the design of ramjet engines,propulsion system performance, turbomachine flow fieldcomputation methods, NASA propulsion controls research, flightmanagement concepts for fuel conservation, blade cascadeaerodynamic losses, viscous transonic flow through cascades, apropulsion system simulation technique for scaled wind tunnelmodel testing, the calculation of secondary flows in an axial flowcompressor, the effect of humidity on compressor performance,vectored thrust nozzles for future combat aircraft, centrifugalcompressor impeller design, turbomachine heat transfer, and gasturbine rotating component life estimation methods O C

445


A83-35806*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioNEW TRENDS IN COMBUSTION RESEARCH FOR GASTURBINE ENGINESE J MULARZ (NASA, Lewis Research Center, CombustionFundamentals Section, U S Army, Propulsion Laboratory,Cleveland, OH) IN International Symposium on Air BreathingEngines, 6th, Paris, France, June 6-10, 1983, Symposium Papers

New York, American Institute of Aeronautics and Astronautics,1983, p 37-44 Army-supported research refs

Research on combustion is being conducted to provideimproved analytical models of the complex flow and chemicalreaction processes which occur in the combustor of gas turbineengines, in order to enable engine manufacturers to reduce thedevelopment time of these concepts The elements of thecombustion fundamentals program is briefly discussed withexamples of research projects described more fully Combustionresearch will continue to emphasize the development of analyticalmodels and the support of these models with fundamental flowexperiments to assess the models accuracy and shortcomingsPreviously announced in STAR as N83-20947 Author

A83-35812#THE EFFECT OF FUEL ATOMIZATION ON SOOT-FREECOMBUSTION IN A PREVAPORIZING COMBUSTORW BUSCHULTE (Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt, Institut fuer chemische Antnebe undVerfahrenstechnik, Hardthausen, West Germany) IN InternationalSymposium on Air Breathing Engines, 6th, Pans, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 79-89 refs

A combustor system with combustion gas recirculation forsoot-free combustion of hydrocarbon fuels with air is describedThe system itself contains - besides means for air supply anddistribution and for fuel supply, atomization and distribution - amixing tube for the introduction of recirculatmg combustion gasinto the air-fuel-mixture stream promoting fuel evaporation and aflame tube for defining a properly sized reactor space Certaininterrelationships between certain measures of the combustorelements are to be obeyed to achieve proper and stable operationSpecial importance for proper functioning was predicted by theoryfor the maximum droplet size in the fuel spray Experimental studieshave been carried out to evaluate the influence of the dropletsize in the spray on sootfreeness of combustion As well dropletsize, fuel-air mixture ratio and fuel viscosity has been varied Theresults show a clearly defined influence of fuel droplet size As asubsidiary result viscosity effects on nozzle flow parameters andmaximum droplet size development are described Author

A83-35820#SEMI IMPLICIT CALCULATION METHOD OF THE FLOW FIELDIN A DUCT WITH THE FLAME STABILIZED BY A STEPP MAGRE (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine,France) IN International Symposium on Air Breathing Engines,6th, Paris, France, June 6-10, 1983, Symposium Papers NewYork, American Institute of Aeronautics and Astronautics, 1983, p147-153 refs

A finite volume semumplicit and fast numerical method forcombustion flow prediction is applied to a problem involving thecoupling of equations, with a view to ensuring computationalstability After performing tests for the validation of computationswithout combustion for the cases of various geometricalconfigurations, the method's suitability for combustion flowphenomena is tested in the case of a premixed flame that isstabilized by a step It is found that, despite the turbulentcombustion model's simplicity, the numerical method is able toprovide a realistic simulation of combustion flow O C

A83-35829#DESIGN AND DEVELOPMENT OF A SMALL GASTURBINEENGINE: RESULTS TODAY - A BASIS FOR DESIGN CRITERIAOF A NEXT GENERATIONH FRICKE and P KOEGEL (KHD Luftfahrttechnik GmbH,Oberursel, West Germany) IN International Symposium on AirBreathing Engines, 6th, Pans, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 231-239

Attention is given to the aerodynamic, thermodynamic, andmechanical design features of the T 117 family of small turbojetengines, which employ a radial compressor and a single turbinestage and exhibit operating cost and reliability improvements over-existing engines of comparable design The T 117 has beencertified for flight after undergoing the flight trials of the CL 289reconnaissance drone, for which it was designed A derivative ofthe T 117, the T 317, is being prepared for flight tests in a newgeneration trainer aircraft O C

A83-35830#PRELIMINARY INVESTIGATION ON THE PERFORMANCE OFREGENERATIVE TURBOFAN WITH INTER-COOLEDCOMPRESSOR AND ITS INFLUENCE TO AIRCRAFTY MIURA (Metropolitan College of Technology, Tokyo, Japan)IN International Symposium on Air Breathing Engines, 6th, Paris,France, June 6-10, 1983, Symposium Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 240-248 refs

A novel intercooler arrangement is proposed for a regenerativeturbofan engine, which promises specific fuel consumptionreductions without incurring thrust deterioration due to core jetvelocity reduction and regenerating system pressure losses Theintercooler heat sinks are cold ram air and fan duct air Calculationsare presented for high and low bypass engines incorporating thepresent regenerator, and calculation results indicate increasedthrust for the high bypass engine Favorable results are alsoobtained by a flight performance study of aircraft equipped withthe regenerative turbofan O C

A83-35831#ON THE PROPULSION SYSTEM OF THE NAL QUIET STOLRESEARCH AIRCRAFTM MORITA, M SASAKI, M MAITA, K TAKASAWA, T TORISAKI,and M MATSUKI (Science and Technology Agency, NationalAerospace Laboratory, Tokyo, Japan) IN International Symposiumon Air Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 249-257 refs

The Japanese National Aerospace Laboratory's Quiet ShortTake-Off and Landing (NAL-QSTOL) experimental aircraft, whosefirst flight is scheduled for 1984, employs an upper surface-blowingpropulsive lift system to achieve the life augmentation required forlow speed STOL operation by means of the Coanda effect TheNAL-QSTOL is powered by four high bypass ratio turbofan enginesrequiring a very complex installation system, with a confluent, longduct exhaust system and a bleed air schedule requiring up to 10percent of the core airflow for such functions as boundary layercontrol, engine nacelle deicing, and cabin air conditioning O C

A83-35832#THE PREDICTION OF PERFORMANCE OF TURBOJET ENGINEWITH DISTORTED INLET FLOW AND ITS EXPERIMENTALSTUDIESD QIUTING, C MENGZI, S HUILI, and C FUQUN (NorthwesternPolytechnical University, Xian, People's Republic of China) INInternational Symposium on Air Breathing Engines, 6th, Pans,France, June 6-10, 1983, Symposium Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 258-262 refs

446


A83-35833#COST EFFECTIVE PERFORMANCE RESTORATION OF HIGHBY-PASS ENGINESR JASPAL and G GREGG (General Electric Co, Cincinnati, OH)IN International Symposium on Air Breathing Engines, 6th, Paris,France, June 6-10, 1983, Symposium Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 263-276 refs

This paper discusses the evolution of engine maintenancepractices and the resultant effects on reduced shop visit ratesand, hence, the engine direct maintenance costs Economicconditions have mandated a reduction in fuel and directmaintenance costs which have resulted in development of costeffective engine maintenance practices Methods developed forcost studies enabled module and engine overhaul time intervalsand also extraordinary performance restoration shop actions tobe defined for the General Electric CF6-50 engines Author

A83-35841#SOME ASPECTS OF DEVELOPMENT OF POWER PLANTOPTIMUM CONTROL TO INCREASE AIRCRAFT FUELEFFICIENCYO K IUGOV (Gosudarstvenny; Institut AviatsionnogoMotorostroenna, Moscow, USSR) IN International Symposiumon Air Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 334-341

This paper outlines the basic principles for optimum powerplant control at different stages of flight The, range of flight istaken as an optimization criterion which represents operationaleffectiveness of the power plant To solve the problem the methodsof optimization are used which are based on the Pontryagmmaximum principle and nonlinear progamming methods Optimumcontrol laws are implemented by introducing electronic power plantcontrol systems and onboard digital computers Author

A83-35842*#INLET, ENGINE, AIRFRAME CONTROLS INTEGRATIONDEVELOPMENT FOR SUPERCRUISING AIRCRAFTJ H HOUCHARD, C M CARLIN, and E TJONNELAND (BoeingMilitary Airplane Co , Seattle, WA) IN International Symposiumon Air Breathing Engines, 6th, Pans, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 342-356 refs(Contract NAS1-16150)

In connection with a consideration of advanced military aircraftsystems, attention is given to research for improving the technologyof the design of supersonic cruise aircraft Syberg et al (1981)have shown that an analytic design method is now available toaccurately predict the flow characteristics of axisymmetncsupersonic inlets, including off-design angle of attack operationOn the basis of information regarding the inlet flow characteristics,the control system designer can begin the inlet design anddevelopment, before wind tunnel testing has begun The presentinvestigation is concerned with details and status of inlet controltechnology A detailed representation of a supersonic propulsionsystem is developed This development demonstrates the feasibilityof the selected hybrid computational concept G R

A83-35843*# Analytical Mechanics Associates, Inc, MountainView, CalifFLIGHT MANAGEMENT CONCEPTS DEVELOPMENT FOR FUELCONSERVATIONJ A SORENSEN (Analytical Mechanics Associates, Inc , MountainView, CA) and S A MORELLO (NASA, Langley Research Center,Flight Management Branch, Hampton, VA) IN InternationalSymposium on Air Breathing Engines, 6th, Pans, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 357-366 refs

It is pointed out that increased airspace congestion will produceincreased flight delay unless advanced flight management conceptsare developed to compensate It has been estimated that a 5percent reduction in delay is approximately equivalent, in terms ofdirect operating costs, to a 5 percent reduction in drag The present

investigation regarding the development of the required flightmanagement concepts is organized into three sections, related tobackground, current research, and future effort In the backgroundsection, a summary is provided of past technical effort concerningflight management The second section is concerned with on-goingefforts to integrate flight management with ground-based flightplanning, and with an advanced concepts simulator to test thenew developments In the third section, attention is given toresearch concerning airborne flight management integration withother flight functions G R

A83-35846#A DYNAMIC MODEL OF TURBOJET IN STARTING AT HIGHALTITUDED-Y YAN and Z-F MAI (Beijing Institute of Aeronautics andAstronautics, Beijing, People's Republic of China) IN InternationalSymposium on Air Breathing Engines, 6th, Paris, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 385-393 refs

A dynamical model for the starting of a turbojet engine isemployed in the computation of the windmilling-to-idling transientprocess, where the model's establishment required both thedefinition of steady state mathematical models of components andthe construction of a dynamic model for the entire powerplantsystem The steady state model presently used for the compressorin the low speed starting region is based on the theory of stageperformance for axial compressors, together with the method offunctional approximation by means of vectonal transformation Themodel is verified in light of the results of both performance testsand digital computations O C

A83-35847#THE TRANSIENT PERFORMANCE OF TURBOJET ENGINESAND AXIAL COMPRESSORSS M RAMACHANDRA, F I ABDELMALIK, and M AMUNTASSER (Alfateh University, Tripoli, Libya) IN InternationalSymposium on Air Breathing Engines, 6th, Paris, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 394-398

Slam acceleration characteristics of turbojet engines determinethe maneuvering performance of military aircraft and the emergencyhandling characteristics of civil aircraft A pair of coupled differentialequations for the rotational speed and the mass flow rate of theturbojet engine is presented together with an algebraic equationfor the compression pressure ratio, giving the overall systemperformance in terms of the component performance Thedifferential equations have been solved analytically assuming anoverall linear performance of the exit jet velocity, the exhaustplane pressure and the thrust It is found that the mass flow ratevariation lags/leads in phase the rotational speedacceleration/deceleration for a non-stationary engine while for thecase of the stationary engine, this phase reverses The thrustvariation follows the mass flow rate variation in a similar mannerAn expression for the characteristic relaxation time of the enginemass flow rate response is given which is also nearly equal tothat of the thrust relaxation time Author

A83-35848#DEVELOPMENT OF A TURBOJET ENGINE SIMULATOR FORSCALE MODEL WIND TUNNEL TESTING OF MULTI-MISSIONAIRCRAFTD J DUSA, C D WAGENKNECHT (General Electric Co,Cincinnati, OH), and T J NORBUT (USAF, Wright AeronauticalLaboratories, Wright-Patterson AFB, OH) IN InternationalSymposium on Air Breathing Engines, 6th, Paris, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 399-407 refs

Conventional wind tunnel test techniques do not providesimultaneous simulation of inlet, airframe and exhaust systemflowfields A propulsion simulator is a miniature jet engine whichenables the correct, or near-correct, simulation of inlet and exhaustsystem flows simultaneously Work on the development of such aminiature jet engine began with the Multi-mission Aircraft Propulsion

447


Simulator (MAPS) in 1969 Encouraged by the successfuldemonstration of the MAPS system's prototype, the developmentof a Compact Multi-mission Aircraft Propulsion Simulator (C-MAPS)began in 1976 C-MAPS incorporates a four-stage compressorand a single turbine stage which is driven by an external highpressure air source Attention is presently given to C-MAPS'sinstrumentation, control console, performance maps, line losses,parasitic flows, and current development status O C

A83-35849#A STUDY OF THE RESPONSE OF A TURBOJET ENGINE TOTHE INLET TEMPERATURE TRANSIENTSD K DAS (New York, State University, Utica, NY), N J SEYB(Rolls-Royce, Ltd , Compressor Research and New Projects Dept,Bristol, England), and A TRIPPI IN International Symposium onAir Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 408-415 refs

The effects of temperature transients on the stability limits ofa turbojet engine fitted with a 15-stage axial flow compressor arestudied by means of a modeling technique in which the engine isseen as a series of ducts whose flow is one-dimensional andunsteady A numerical technique based on the method ofcharacteristics has been used to solve the conservation equationsand the first order, ordinary differential equation introduced to modelthe compressor's dynamic response The model is applied to thesimulation of engine response to the mgestion of planar entropywaves due to fast temperature ramps at the system inlet Theevents leading up to the engine's surge and stability limits, aspredicted by the model, compare well with both qualitative andquantitative experimental values from the literature O C

A83-35854#EFFECT OF SAND EROSION ON THE PERFORMANCEDETERIORATION OF A SINGLE STAGE AXIAL FLOWCOMPRESSORW TABAKOFF and C BALAN (Cincinnati, University, Cincinnati,OH) IN International Symposium on Air Breathing Engines, 6th,Pans, France, June 6-10, 1983, Symposium Papers New York,American Institute of Aeronautics and Astronautics, 1983, p458-467 refs(Contract DAAG29-82-K-0029)

Aircraft engines operating in areas where the atmosphere ispolluted with small solid particles are subjected to performancedeterioration Improvement in performance deterioration canprolong the engine life and save operating expenses Such animprovement is possible only by understanding the basicmechanism of erosion and the associated performancedegradation This paper presents experimental work carried outon two-dimensional compressor cascades along with a theoreticalmodel to predict the performance deterioration of cascadessubjected to erosion In addition investigations are carried out ona single stage axial flow compressor to study the effect of erosionon performance Author

A83-35856*# Purdue Univ, Lafayette, IndEFFECT OF HUMIDITY ON JET ENGINE AXIAL-FLOWCOMPRESSOR PERFORMANCEC M EHRESMAN, S N B MURTHY, and T TSUCHIYA (PurdueUniversity, West Lafayette, IN) IN International Symposium onAir Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 479-486 refs(Contract NAG3-62, NAG3-204, F33615-78-C-2401)

Two problems related to the mgestion of humid air into jetengine axial compressors have been studied (1) the changes inthe performance of the compressor in the absence of condensationand (2) the changes in the entry conditions to the compressorwhen condensation occurs Regarding the first, the extent ofchanges are predicted and also measured in the case of a six-stagecompressor operated with air-methane gas mixture utilizing thesimilarities in the thermodynamic properties between water vaporand methane For the condensation process in an inlet, a model

is described that takes into account the presence of microparticulates and the flow field changes in the vicinity of the inletwall Finally, the effects of humidity on engine performance arediscussed in relation to engine trim and control schemes Author

A83-35858*STATISTICAL STUDY OF TBO AND ESTIMATION OFACCELERATION FACTORS OF ASMT FOR AIRCRAFTTURBO-ENGINEY -M ZHANG (Shanghai Aviation Industry Corp , Shanghai,People's Republic of China) IN International Symposium on AirBreathing Engines, 6th, Paris, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 499-509 refs

BASIC computer language methods are presented for theanalysis of aircraft engine TBO, together with reliability On thebasis of both a linear cumulative damage principle and the equalityof safety load factors, a method of estimating the accelerationfactor of components whose operating lives are determined bycreep rupture stress, low cycle fatigue, contact stress and highcycle fatigue is given The estimation of the optimal maximumacceleration factor is based on a least squares method, and showsthat the accelerated simulation mission test controllable parameterswill gain in engine acceleration factor O C

A83-35859#VECTORED THRUST AFTERBODY NOZZLES FOR FUTURECOMBAT AIRCRAFTM DREVILLON and R FER (SNECMA, DepartementAerodynamique, Moissy-Cramayel, Seine-et-Marne, France) INInternational Symposium on Air Breathing Engines, 6th, Paris,France, June 6-10, 1983, Symposium Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 510-518

Comparative experimental study results are presented for thrustvectoring afterbody nozzles applicable to future combat aircraft,where the baseline design is an axisymmetric nozzle mounted ona spherical flange at the end of the afterburner Static performancehas been measured on a mock-up with pressure ratios of up to8 1 Configurations representative of dry and afterburning engineoperation have also been tested, with vectoring angles of up to20 deg An analysis of internal flow characteristics and interferencewith afterbody flaps is undertaken, and consideration is given tothe potential future applications of thrust vectoring nozzles O C

A83-35865#CONTRIBUTION TO CENTRIFUGAL COMPRESOR IMPELLERDESIGNV VANEK (Vyzkumny a Zkusebni Letecky Ustav, Prague,Czechoslovakia) IN International Symposium on Air BreathingEngines, 6th, Paris, France, June 6-10, 1983, Symposium Papers


A part of centrifugal compressor impeller pre-developmentresearch program is described The investigation results of theset of radially bladed impellers designated the ARTI 305 arediscussed The impellers were designed for identical initial andboundary conditions Space shapes of the impellers blading aredifferent The impellers blading geometry is defined by two so-calleddeceleration coefficients Experimental investigation was arrangedto verify the impeller design and manufacture method and influenceof the impeller blading space shape on its performance map

Author

A83-35866#THE EFFECT OF VARIATION OF DIFFUSER DESIGN ON THEPERFORMANCE OF CENTRIFUGAL COMPRESSORSA M EL SIBAIE (Am Shams University, Cairo, Egypt) and M HNASSAR (Egyptian Air Force, Cairo, Egypt) IN InternationalSymposium on Air Breathing Engines, 6th, Paris, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 571-578 refs

Attention is given to the effect of the number of diffuser vanes,vane curvature, and diffuser rotation, on the performance of a

448


centrifugal compressor applied to an aviation piston engine Diffuservane number and curvature have direct effects on compressorstage performance and diffuser efficiency, where the controllingfactor is the ratio of overlap area between two successive vanesand the number of diffuser vanes Diffuser efficiency andcompressor pressure ratio increase with this ratio By rotating thediffuser with the same angular velocity as the impeller, a higherpressure ratio was obtained for the compressor, together with awider mass flow rate range O C

A83-35869#COMPONENT LIFE REDUCTION DUE TO USE OF AVGAS INGAS TURBINE ENGINESM L SIDANA and K SRINIVASA (Ministry of Defence, Directorateof Aeronautics, Bangalore, India) IN International Symposiumon Air Breathing Engines, 61h, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 597-602

Attention is given to the effects of the use of AVGAS fuelengines designed for operation on AVTUR fuels, with the intentionof assessing the effects of the fuel change on fuel pump and hotsection component service lives Erosion rate, crack growth rate,and burn areas were monitored, and the effect of erosion onturbine blade fatigue and creep life was analyzed and found to belife-limiting Low lubricity and higher vapor pressure also adverselyaffected fuel pump life O C

A83-35870#LIFE ESTIMATION METHODS OF GAS TURBINE ROTATINGCOMPONENTSJ S RAO (Bharat Heavy Electncals, Ltd, Hyderabad, India) INInternational Symposium on Air Breathing Engines, 6th, Paris,France, June 6-10, 1983, Symposium Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 603-610 refs

An expression is derived for the computation of the equivalentcyclic damage rate of compressor and turbine disk spacers andshafts subjected to low cycle fatigue, where the fatigue is due tothe cyclic loading which arises with engine speed changes Theexpression allows gas turbine designers to predict the low cyclefatigue life of rotating components in light of the assumed flightenvelope of an aircraft A method is also given for the assessmentof compressor blade life, which is based on a residual strengthplot derived from the rig fatigue testing of blades O C

A83-35871#CONTAINMENT OF TURBINE ENGINE FAN BLADESJ M PAYEN (SNECMA, Departement Mecamque Avancee,Moissy-Cramayel, Seme-et-Marne, France) IN InternationalSymposium on Air Breathing Engines, 6th, Pans, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 611-616

Presented are an analysis of the gas turbine engine fan bladefragmentation process, an evaluation of blade fragment energy,an investigation of the fan casing performation mode, and thedevelopment of a stressing method applicable to metal containmentcasings which makes use of Kevlar fabric The metal casingstressing model employed is based on the theory of dynamicshearing perforation Tests simulating blade fragment impacts onKevlar fabric strips were used to investigate fabric behavior andto define a method for the computation of the number of fabriclayers required to achieve containment O C

A83-35872#A CONTRIBUTION TO AIRWORTHINESS CERTIFICATION OFGAS TURBINE DISKSJ DREXLER and J STATECNY (Vyzkumny a Zkusebni LeteckyUstav, Prague, Czechoslovakia) IN International Symposium onAir Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 617-622

Airworthiness proof of gas turbine disks involves some specificproblems connected with the experimental verification of theadmissible probability of a hazardous effect due to an individual

failure The authors' attempt is to present a simple method howto meet the airworthiness requirements in case that the disk bladefir-tree attachment number exceeds some tenths, the dominatingdamage mechanism being low cycle fatigue The structure of themethod consists in taking the disk operation or test as anexperiment being run simultaneously on a group of identical testspecimens up to appearances of the cracked attachmentcumulative numbers describing achievement of the disk limitstate Author

A83-35879#INVESTIGATION METHODS ON RESIDUAL STRESSES IN AEROENGINES COMPONENTSJ KAFKA, F NECKAR (Ceske Vysoke Uceni Technicke, Prague,Czechoslovakia), D SMETANA, and P VOSTATEK (Motorlet,Prague, Czechoslovakia) IN International Symposium on AirBreathing Engines, 6th, Pans, France, June 6-10, 1983, SymposiumPapers New York, American Institute of Aeronautics andAstronautics, 1983, p 677-683 refs

Methods and obtained results are presented for themeasurements of residual stresses in surface layers of chromiumsteel and titanium alloy materials used in the fabrication of axialcompressor vanes and impellers for a small turboprop engineThe measurements were conducted in order to increase bothservice life and reliability and fabrication process productivity Inthe case of compressor vanes, the connection between residualstress magnitude and fatigue limit is established Surface layerresidual stress magnitude and character, after titanium alloy millingand finishing operations, were measured through the destructivemethod of electrochemical removal from the specimen surfacewhile recording deformation O C

A83-35880#STRESS ANALYSIS OF CRITICAL AREAS OF LOW-PRESSURECOMPRESSOR-DISC ASSEMBLY OF A DEVELOPMENTALAERO-ENGINER PADMANABHAN, K RAMACHANDRA, B J RAGHUNATH, andV MARUTHI (Gas Turbine Research Establishment, Bangalore,India) IN International Symposium on Air Breathing Engines,6th, Paris, France, June 6-10, 1983, Symposium Papers NewYork, American Institute of Aeronautics and Astronautics, 1983, p684-691

A series of three-dimensional photoelastic investigations hasbeen conducted in order to estimate the strength reserve factorsof compressor blades and disks which employ lugs for attachmentAttention is given to the influence of untwisting torque of widechord and large twist blades on the stresses at the concave andconvex profile fillets of blade aerofoil roots, together with thecombined effect of large axial loads, rim-bending loads, and hooploads, on stress concentration factors around the cutouts in thecompressor disk rims Concave profile stresses as high as 5 8times greater than those theoretically obtained for the root filletsof first stage blades are noted It is also confirmed that the influenceof lug axial loads on disk stress concentration factors, under normaloperating conditions, is not as significant as the radial rim loads

OC

A83-35881#EXCITATION AND VIBRATION OF FLEXIBLE BLADED DISKSUNDER OPERATING AND SIMULATED OPERATIONCONDITIONSZ DOLEZAL (Vyzkumny a Zkusebni Letecky Ustav, Prague,Czechoslovakia) IN International Symposium on Air BreathingEngines, 6th, Paris, France, June 6-10, 1983, Symposium Papers


Theoretical and experimental investigation results are presentedfor bladed disk assembly vibration characteristics, with attentionto those of impellers The formulas obtained for the exciting rotatingvectors connected with an engine's internal operating conditionsare used for the prediction and analysis of forced vibration, andfor the simulation of the operating excitation Knowing the excitationand dynamical property rotating vectors of a bladed disk, the

449


resonances occurring under the given operating conditions maybe predicted Experimental results are given for the dynamicresponses of impellers that prove the theoretical solution'svalidity O C

A83-35882#VARIATION OF ROTOR BLADE VIBRATION DUE TOINTERACTION OF INLET AND OUTLET DISTORTIONS YOKOI, S NAGANO (Ishikawajima-Harima Heavy Industries Co ,Ltd, Aero-Engine and Space Development Group, Tokyo, Japan),and T ABE (Japan Defense Agency, Technical Research andDevelopment Institute, Tokyo, Japan) IN International Symposiumon Air Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 700-707

The variation of rotor blade vibration due to the interaction ofinlet and outlet distortion is experimentally investigated by meansof a two-stage fan with a typical circumferential distortion screenThe vibration level of the first and second stage rotor blades, andthe pressure distributions upstream and downstream of the secondstage, were investigated and compared for various screencircumferential positions In the case of combined inlet distortions,the distortion levels significantly changed according to screencircumferential position In the case of combined inlet and outletdistortions, inherent inlet distortion was nearly compensated forby outlet distortion for any screen position, and also yielded aconstant blade vibration level O C

A83-35883*# Princeton Univ , N JDESIGN OF DRY-FRICTION DAMPERS FOR TURBINEBLADESW ANCONA and E H DOWELL (Princeton University, Princeton,NJ) IN International Symposium on Air Breathing Engines, 6th,Pans, France, June 6-10, 1983, Symposium Papers New York,American Institute of Aeronautics and Astronautics, 1983, p708-722 refs(Contract NAG3-221)

A study is conducted of turbine blade forced response, wherethe blade has been modeled as a cantilever beam with a generallydry friction damper attached, and where the minimization of bladeroot strain as the excitation frequency is varied over a given rangeis the criterion for the evaluation of the effectiveness of the dryfriction damper Attempts are made to determine the location ofthe damper configuration best satisfying the design criterion,together with the best damping force (assuming that the damperlocation has been fixed) Results suggest that there need not bean optimal value for the damping force, or an optimal location forthe dry friction damper, although there is a range of values whichshould be avoided O C

A83-36236#CRITERIA FOR OPTIMIZING STARTING CYCLES FOR HIGHPERFORMANCE FIGHTER ENGINESJ B DAVIS and R R POLLAK (United Technologies Corp,Government Products Div, West Palm Beach, CA) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 12 p(AIAA PAPER 83-1127)

This paper summarizes some of the criteria that must beconsidered to optimize starting cycles for modern fighter aircraftengines Due to high performance compression system designs,the ability to start successfully has become more challenging Theeffects of major variables that influence starting ability arediscussed together with a description of improved techniques thatare now available to quantify these variables As a result of thesedevelopment efforts and the advent of fully electronic controlsystems, a unique, closed-loop starting system that has beendesigned and developed to provide consistency to the startingcycle regardless of external or internal conditions of the engineare discussed Author

A83-36238#SIMULATION OF ADVANCED ENGINE LUBRICATION ANDROTOR DYNAMICS SYSTEMS - RIG DESIGN ANDFABRICATIONA PEDUZZI (United Technologies Corp, Government ProductsDiv , West Palm Beach, FL) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 9 p(AIAA PAPER 83-1133)

Advanced technology dual rotor turbofan and turbojet engineswill incorporate rotor support system features to increase rotorspeed capability and engine thrust-to-weight ratio while reducingcost These features may include straddle-mounted rotors, highstrain energy low pressure rotors and counter-rotating shafts witha load-carrying mtershaft bearing A 'bladeless engine' rigincorporating the above features has been designed and fabricated,and test plans formulated The rig will be utilized to evaluate counterrotating mtershaft bearing lubrication and breather systemoperation, low leakage mtershaft seals, and dynamic operation ofcounter-rotating rotors including identification of critical speedmodes, shaft deflection and bearing load sensitivity to rotorimbalance, as well as oil film damper operation Pre-test calibrationsof damper sprmgrate and high and low rotor resonant frequencieswere conducted System endurance will be evaluated in a 150-hourcyclic endurance test Author

A83-36244#EFFECT OF FUEL COMPOSITION ON NAVY AIRCRAFT ENGINEHOT SECTION COMPONENTSR E VOGEL, S B REIDER (General Motors Corp , Detroit DieselAllison Div, Indianapolis, IN), and P A KARPOVICH (U S NavalAir Propulsion Center, Trenton, NJ) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 19838 p Navy-supported research(AIAA PAPER 83-1147)

Fuel composition is examined with a view to relaxing fuelspecifications and thus increasing the supply of gas turbine fuelThe tests are carried out on the T56 aircraft engine, whosecombustion system is described The effect of variation in fuelproperties is evaluated by testing 10 experimental fuels in asingle-can combustion rig The rig simulates a 60-deg sector ofthe T56 engine combustion system from diffuser inlet to turbineinlet, this includes the compressor discharge passage, the diffuserair passage, the inner and outer cases, and the turbine inletpassage The T56-A-14 combustion system is found in general tobe highly tolerant of broadened fuel specifications It is believedthat the limitations imposed on the ignition/lean blowout capabilitycould be removed or reduced by modifications to the fuel injectordesign The incidence of a strong statistical correlation betweenfuel properties and combustor performance is found to be muchhigher at low power (idle, altitude cruise) than that at high power(climbout, takeoff) Another finding is that low-power gaseousemissions are influenced by physical fuel properties (distillation,viscosity, freeze point, pour point) No significant fuelproperty-emission correlations are found at high power C R

A83-36250*# General Motors Corp , Indianapolis, IndADVANCED PROPFAN ENGINE CHARACTERISTICS ANDTECHNOLOGY NEEDSR D ANDERSON, J C GILL, and A S NOVICK (General MotorsCorp, Indianapolis, IN) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 9 p(Contract NAS3-23046)(AIAA PAPER 83-1155)

A comparative study is presented for two of the advanced gasturbine engine designs developed in the course of a proprietaryresearch effort for the NASA Advanced Propfan Engine Technologyresearch program In these engines, a cycle pressure ratio of32 5 1 and a 2500 F maximum turbine temperature provide fuelefficient operation in the 32,000-ft altitude, Mach 0 72 cruise speedregime stipulated Both of the engine configurations incorporatethree spools, of "which the compressors are dual-spool and thepower turbines are free A major design challenge for axial

450


compressors in the 10,000-shp class was the maintenance ofadequate blade heights in the later stages O C

A83-36251#THE PERFORMANCE OF SINGLE-SHAFT GAS TURBINE LOADCOMPRESSOR AUXILIARY POWER UNITSC RODGERS (Solar Turbines, Inc, Turbomach Div, San Diego,CA) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 8 p refs(AIAA PAPER 83-1159)

Military and commercial aircraft operating from remote airfieldscan attain self-sufficiency with small onboard auxiliary power units(APU) When large amounts of pneumatic ground power arerequired for aircraft systems cooling at hot day conditions in additionto self-start capability, the optimum APU is that which can provideair for the environmental control system and to an air turbinestarter Three gas turbine APU configurations are used to supplyessentially 100 percent pneumatic power output They include thesingle-shaft gas turbine integral bleed (SSGTIB), the single-shaftgas turbine load compressor (SSGTLC), and the two-shaft gasturbine load compressor The SSGTIB has dominated thepneumatic APU field for two decades Recently, the SSGTLC hasentered the U S pneumatic power APU market The SSGTLC hasoperational characteristics which are different from those of theSSGTIB Attention is given to relevant information on the SSGTLCAPU characteristics This information can be used for secondarypower tradeoff studies by the aircraft-user G R

A83-36252*# General Electric Co , Cincinnati, OhioTHE AERODYNAMIC DESIGN AND PERFORMANCE OF THEGENERAL ELECTRIC/NASA EEE FANT J SULLIVAN (General Electric Co, Cincinnati, OH) and R DHAGER (NASA, Lewis Research Center, Cleveland, OH) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 11 p refs(AIAA PAPER 83-1160)

The aerodynamic design and test results of the fan andquarter-stage component for the GE/NASA Energy Efficient Engine(EEE) are presented The fan is a high bypass ratio, single-stagedesign having 32 part-span shrouded rotor blades, coupled with aunique quarter-stage arrangement that provides additionalcore-stream pressure ratio and particle separation The fanproduces a bypass pressure ratio of 1 65 at the exit of the lowaspect ratio vane/frame and a core-stream pressure ratio of 1 67at the entrance to the core frame struts The full-scale fan vehiclewas instrumented, assembled and tested as a component inNovember 1981 Performance mapping was conducted over arange of speeds and bypass ratios using individually-controlledbypass and core-stream discharge valves The fan bypass andcore-stream test data showed excellent results, with the fanexceeding all performance goals at the important engine operatingconditions Author

A83-36253#DESIGN AND PERFORMANCE OF A LOW ASPECT RATIO, HIGHTIP SPEED MULTI-STAGE COMPRESSORW A TESCH and R L PASE (United Technologies Corp ,Government Products Div, West Palm Beach, FL) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 8 p(AIAA PAPER 83-1161)

The aerodynamic design and performance of a low aspectratio, high tip speed multi-stage axial compressor for applicationin turboshaft engines is presented The axial compressor has beendesigned to be used in conjunction with a centrifugal stage toproduce the required cycle pressure ratio Designed to produceabove 7 to 1 pressure ratio, the compressor is comprised of fiveaxial stages and features variable geometry to meet the off-designstability requirements The average aspect ratio and solidity are1 2 and 1 6, respectively Considerations as a result of the presenceof a centrifugal stage and the mechanical arrangement of -theengine are discussed The compressor has been evaluatedexperimentally as a component rig powered by a 6000 hp electric

motor Testing encompassed 153 hours of running over the entireanticipated operational regime At design speed, the compressorhas demonstrated a peak adiabatic efficiency above 85 percentand a stall margin above 20 percent Author

A83-36254#MAXIMUM LOADING CAPABILITY OF AXIAL FLOWCOMPRESSORSJ K SCHWEITZER and J E GARBEROGLIO (United TechnologiesCorp , Government Products Div , West Palm Beach, FL) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 10 p refs(Contract F33615-76-C-2091)(AIAA PAPER 83-1163)

A maximum loading prediction system for determining the designspeed stall margin capability of axial flow compressors is presentedThe formulation of the primary correlations for this system is basedon the analogy between a compressor cascade and a diffuserpassage Semi-empirical corrections are applied to relate the initialcascade-derived maximum loading values to the real compressorenvironment Good agreement is demonstrated between thepredicted and test stall margins for a wide range of both smgle-and multi-stage compressor geometries As the system isformulated on the basis of meanlme parameters, a useful toolhas resulted capable of guiding the selection of the primarycompressor design variables early in the design phase Author

A83-36260#A SURVEY OF TRENDS IN MODERN TURBINE TECHNOLOGYK D MACH and D W ZABIEREK (USAF, Aero PropulsionLaboratory, Wright-Patterson AFB, OH) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 19833 p(AIAA PAPER 83-1174)

In connection with the development of component technology,there exists a potential for dramatic increases in turbineperformance Advances are needed with respect to materials, heattransfer, and aerodynamics An important contribution to theimprovement of material characteristics can be provided by suitablecoatings To survive in an environment of high-temperature gas, amaterial will need protection against oxidation, corrosion, anderosion Extensive development work with respect to coatings is,therefore, expected through the end of the century Except forcoatings, turbine vanes and blades will continue to be made ofmetal for the next several years The most serious drawback ofceramics, brittleness, has not yet been overcome Of the metals,the refractories are the least developed for turbine applicationswith respect to conventional superalloys, very little room remainsfor further development Extensive studies and development workduring the next decade will be concerned with heat transfer, cooling,and aerodynamic design G R

A83-36261*CRUISE MISSILE PROPULSION VERSUS COMMERCIALAIRLINER PROPULSION - DIFFERENT CHALLENGES CANPRODUCE SIMILAR ENGINE CYCLESL CRUZEN (Williams International, Walled Lake, Ml) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 6p refs(AIAA PAPER 83-1176)

A commercial turbofan engine, the JT8D, which is employedto power a number of airliners, is compared with F107 engines,which power the Air Force and Navy cruise missiles The designrequirements for aircraft and cruise missile propulsion systemsare examined It is found that a cruise missile and a commercialairliner engine do not share many of the major parameters whichinfluence cycle selection The airliner application tends to call forhigher bypass ratio and, consequently, for higher turbine inlettemperatures However, an inspection of relevant design datashows that JT8D and F107 cycle parameters are notably similar,although the JT8D-17 engine is about 24 times the size of theF107-WR-101 In this connection, questions arise regarding thereasons for the low bypass ratio employed by the JT8D-17 cycle

451


It is shown that the JT8D-17 characteristics are the results ofevolutionary changes G R

A83-36282#CONCEPTS FOR INCREASED POWER AND ENHANCED FUELCONSERVATION WITH NEWLY PATENTED MULTIPLEPOWER-CYCLE GAS TURBINE ENGINESP K CORONEL AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 6 p(AIAA PAPER 83-1209)

Attention is given to recently pattented design innovations aimedat improving the fuel efficiency and power output of axial andcentrifugal compressor-equipped gas turbine engines The systemsdisclosed integrally incorporate secondary power cycles containingheat absorption systems which convert unpressunzed liquids intoa pressurized power source, employing the heat energy normallylost through component cooling systems and the engine exhaustThis heat energy is recycled to power a steam turbine, which inturn is employed in increasing the gas turbine's volume of preheatedand compressed air In addition to greater propulsive and fuelefficiencies, a reduction of exhaust heat is envisaged O C

A83-36293#THRUST REVERSER EXHAUST PLUME REINGESTION TESTSFOR A STOL FIGHTER MODELN F AMIN and C J RICHARDS (Northrop Corp, Hawthorne,CA) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 11 p(AIAA PAPER 83-1229)

The development of advanced tactical fighter aircraft requiringshort takeoff and landing capabhty in order to operate from bombdamaged runways is being considered A STOL aircraft with areversing nozzle may be needed to satisfy this requirement Thrustreversing represents an effective approach for decelerating anaircraft, both in-flight and during ground roll A potential problemassociated with reversing thrust during aircraft ground roll is relatedto the mgestion of hot exhaust gases into the engine inlet Theremgested gases can generate pressure and temperature distortionlevels at the engine compressor face substantially above the enginedistortion tolerance limits, resulting in possible engine damage Itis found that for an effective thrust reverser design, it is necessaryto develop a detailed exhaust plume remgestion test data baseAttention is given to a novel flow visualization water and windtunnel test program which was conducted to develop the requireddata base G R

A83-36284#ADVANCED TURBOPROP AND DUAL CYCLE ENGINEPERFORMANCE BENEFITS AND INSTALLATION OPTIONS ONA MACH 0 7 SHORTHAUL TRANSPORT AIRCRAFTH W BENNETT (Rolls-Royce, Ltd , Derby, England), A P HAYS,and G L HERSTINE (Lockheed-California Co, Burbank, CA)AIAA, SAE, and ASME, Joint Propulsion Conference, 19th, Seattle,WA, June 27-29, 1983 12 p refs(AIAA PAPER 83-1212)

The block fuel and direct operating costs of a 100 passengeraircraft powered by an advanced turbofan, turboprop, and a dualcycle engine were evaluated The locations of the turbopropengines were also evaluated based on aircraft weight, drag, andinlet recovery penalties Results show that the underwmg mountedturboprop engine with offset gearbox and chin inlet was theoptimum configuration The turboprop is found to have a blockfuel advantage of 27 percent over the turbofan at the averagestage length of 300 n mi and a 26 percent advantage at thedesign range of 1000 n mi The direct operating cost benefit wasdetermined to be 16 percent at the average stage length Thedual cycle engine exhibited a block fuel benefit of only 22 percentat the average stage length and 21 percent at the design range,while the direct operating cost benefit was 12 percent at theaverage stage length N B

A83-36286*# National Aeronautics and Space AdministrationFlight Research Center, Edwards, CalifIN-FLIGHT ACOUSTIC TEST RESULTS FOR THE SR-2 ANDSR-3 ADVANCED-DESIGN PROPELLERSP L LASAGNA, K G MACKALL, and R B COHN (NASA, FlightResearch Center, Edwards, CA) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 9 prefs(AIAA PAPER 83-1214)

Several advanced-design propellers, previously tested in thewind tunnel at the Lewis Research Center, have been tested inflight at the Dryden Flight Research Facility The flight-testpropellers were mounted on a pylon on the top of the fuselage ofa JetStar airplane Acoustic data for the advanced-design SR-2and SR-3 propellers at Mach numbers to 0 8 and helical-tip Machnumbers to 1 15 are presented, maximum blade-passage frequencysound-pressure levels are also compared Author

A83-36294#A MONTE CARLO SIMULATION OF THE ENGINEDEVELOPMENT PROCESSW R ALLEY, JR and H D STETSON (United TechnologiesCorp , Government Products Div , West Palm Beach, FL) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 8 p(AIAA PAPER 83-1230)

A mathematical model of the engine development process hasbeen formulated The model quantifies the elements that affectengine development, such as test vehicles, severity and length oftests and test schedule Problem occurrences, based on historicexperience, are introduced at random by the model and the impactof these problems on the development program is assessed Byiterating a given development plan, a statistical distribution ofprobable program results, including such information as programduration, problems found, and engine maturity at fleet introductionis obtained Modifying the development plan input and re-runningthe program generates a new set of probable program resultswhich can be compared with the original results to evaluate theadvantages and disadvantages of each plan A typical enginedevelopment program was modeled and several perturbations ofthe development plan were made and evaluated Author

A83-36295#NONDESTRUCTIVE EVALUATION METHODS FORIMPLEMENTATION OF DAMAGE-TOLERANT DESIGNED GASTURBINE ENGINE COMPONENTSV E PANHUISE (Garrett Turbine Engine Co , Phoenix, AZ) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 5 p(AIAA PAPER 83-1232)

In connection with the development of engines for the U S AirForce, use is made of the 'Engine Structural Integrity Program'(ENSIP) which is based upon damage-tolerant design assessmentsUsing ENSIP, a critical rotating component is designed with theassumption that a flaw could be present in the component Atcertain time intervals, the component is inspected to detect flawswhose size exceeds a predetermined threshold If none is found,the part is returned to service However, if a flaw is detected, thecomponent will be 'retired for cause' (RFC) A review is providedof the nondestructive evaluation (NDE) techniques used duringENSIP-designed component fabrication, taking into account alsothe methods by which the reliability of each technique are to bedemonstrated G R

452


A83-36296#AIRCRAFT ENGINE INLET PRESSURE DISTORTION TESTINGIN A GROUND TEST FACILITYR E ANDERSON (U S Naval Air Propulsion Test Center, Trenton,NJ) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 12 p refs(AIAA PAPER 83-1233)

At first, the problem of inlet distortion as it affected the stabilityof a jet engine in a high performance aircraft was eitherunderestimated or not understood Inlet pressure distortionphenomena can be divided into steady-state and time-variantcategories A review is provided of various methods for producingeach type Steady-state pressure distortion is the relatively constantpressure variation from the average pressure of the measurementplane A variation from the center to the outside diameter is calledradial distortion, while circumferential distortion represents variationon any concentric circle Steady-state total pressure distortion fortest purposes is generally produced by screens Attention is givento a distortion valve, distortion screens for steady-state pressurepatterns, aspects of screen design, design revisions, themeasurement of steady-state distortion, time-variant distortion, andrandom frequency generators G R

A83-36297#DETERIORATION TRENDING ENHANCES JET ENGINEHARDWARE DURABILITY ASSESSMENT AND PARTMANAGEMENTR J BARRETT (United Technologies Corp , Government ProductsDiv, West Palm Beach, FL) and W R HARRIS, JR (U S NavalAir Systems Command, Propulsion Div , Washington, DC) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 6 p(AIAA PAPER 83-1234)

The exposure of a new aircraft engine to the serviceenvironment can reveal engine hardware durability limitations notevident during the development or model acceptance phase ofan engine program In connection with the recognition by the Navyof the need for an improved full-scale engine test to assure thelong-range durability characteristics of the engine, a new approachfor assessing engine hardware durability improvements was initiatedin 1978 The approach included Accelerated Simulated MissionEndurance Test (ASMET) and fleet engine hot section hardwaredeterioration comparisons Part deterioration 'trending' was initiatedduring ASMET engine hot section inspections in order to establisha baseline of trending data for comparison with fleet hardware Itis pointed out that jet engine hardware deterioration trending isnow a proven method for enhancing long-term durability evaluationof new and improved hardware designs G R

A83-36298#ACCELERATED MISSION TESTING OF THE F110 ENGINEO T CASTELLS (General Electric Co, Evendale, OH) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 7 p(AIAA PAPER 83-1235)

A summary of the new use of Accelerated Mission Testing(AMT), in the development of the F110 Engine (formerly F101DFE), is presented A comparison of the AMT to previousqualification tests and to actual field service is presented Thistest approach has been now adopted as the official endurancequalification test for the USAF Author

A83-36299#INTEGRATED PROPULSION-AIRCRAFT CONTROLEVALUATION FOR A CURRENT NAVY FIGHTERR W VIZZINI (U S Naval Air Propulsion Test Center, AdvancedDevelopment Div, Trenton, NJ) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 12p refs(AIAA PAPER 83-1236)

It is pointed out that the Navy is actively engaged in thedevelopment of engine-mounted, fault tolerant Full Authority DigitalElectronic Controls (FADEC) This technology base will lead to

advanced propulsion control systems integrated with aircraft controlsystems to provide a wider range of aircraft-engine optimizationthan is available today The present investigation is concernedwith the major benefits of an advanced control system integratedwith the F-14 aircraft A TF30 engine with a dual-channel, faulttolerant FADEC has been interfaced to an Advanced FuelManagement (AFM) system It is shown that overall F-14 propulsionsystem reliability would be improved by at least a factor of twodue to the integration of the FADEC/AFM configuration with theF-14 control system Other benefits included improvedaircraft-engine performance and significant reductions in aircraftsystem weight, cost, and fuel consumption G R

A83-36300#F/A-18A INFLIGHT ENGINE CONDITION MONITORING SYSTEM(IECMS)P M DOANE (McDonnell Aircraft Co, St Louis, MO) and W RKINLEY (General Electric Co, Lynn, MA) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 198310 p(AIAA PAPER 83-1237)

An Inflight Engine Condition Monitoring System (IECMS) hasbeen developed by General Electric and McDonnell Aircraft andis currently operational in all F/A-18 aircraft It is fully integratedwith other systems on the aircraft, minimizing cost and weightThe system activates cockpit cautions and sets maintenance codeswhenever an engine exceedance is detected Engine data isautomatically recorded up to 5 seconds before the exceedanceand 35 seconds after In addition, engine life usage parameters,used for tracking remaining engine life, are calculated in flightOperational experience has shown benefits in reducedmaintenance, lower support costs and accelerated maturing ofthe engine Specific cases illustrating these benefits are describedA list of design considerations, based on IECMS experience, ispresented for application to future systems Author

A83-36301#FLIGHT/PROPULSION CONTROL SYSTEM INTEGRATIONL D EMERSON and W J DAVIES (United Technologies Corp,Pratt and Whitney Group, West Palm Beach, FL) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 6 p(AIAA PAPER 83-1238)

In connection with the introduction of redundant digital electronicsystems to accomplish flight and propulsion control in modernmilitary aircraft, opportunities arise for complete weapons systemsintegration Attention is given to system intercommunication, thecommunication of thrust request to the engine control on theelectronic data bus, the engine condition monitoring system(ECMS), the electrical power system, and the design of hydraulicpower systems on advanced aircraft and propulsion systems It isshown that integrated aircraft and propulsion control systemsprovide the key to many benefits for future aircraft Integratedcommunications lead to improved weapon system performance,increased reliability, ease of maintenance, and cost and weightbenefits Shared electric and hydraulic power can provide similarbenefits G R

A83-36302#UNITED KINGDOM MILITARY ENGINE USAGE, CONDITIONAND MAINTENANCE SYSTEMS EXPERIENCEM F HURRY (Ministry of Defence/Procurement Executive/,London, England) and C M OCONNOR (Rolls-Royce, Ltd , Bristol,England) AIAA, SAE, and ASME, Joint Propulsion Conference,19th, Seattle, WA, June 27-29, 1983 10 p(AIAA PAPER 83-1239)

The engine monitoring systems and programs used in the U Kfor military aircraft are reviewed An engine usage monitoringsystem was installed on numerous aircraft in 1975 and coversengme/airframe instrumentation, data acquisition, and ground dataprocessing The data acquisition system is capable of multiplexingand digitizing signals at a rate of 32 twelve-bit words per secondThe taped data is processed on the ground by mainframe

453


computers The initial systems used sensors connected tomicroprocessors to monitor the LP shaft speed, the HP shaft speed,compressor delivery temperature, and compressor temperature,the exhaust gas temperature and duct pressure, the turbine coolingair temperature, the throttle valve angle, fuel flow, the enginecontrol amplifier current, vibration, altitude, airspeed, ambienttemperature, and the elapsed time A magnetic chip is employedfor monitoring oil-wetted engine components M S K

A83-36304#COMPARISON OF AN EXPERIENCE WITH FULL AUTHORITYDIGITAL ENGINE CONTROLS IN ROTARY WING AND JET-LIFTVSTOL AIRCRAFTE S ECCLES (Dowty and Smiths Industries Controls, Ltd ,Cheltenham, Glos, England) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 9 pResearch supported by the Ministry of Defence of England refs(AIAA PAPER 83-1241)

The design differences and common features of the full authoritydigital engine control demonstrator systems mounted on the Gemengines in a Lynx helicopter and on the Pegasus engines in aHarrier aircraft are surveyed The Gem system contained its ownpower supply, while the Pegasus system was connected to theaircraft power supplies The Gem system, being on a helicopter,had lower static and dynamic pressures to contend with, but wasrequired to be able to disconnect the engine from the rotor whena rapid onset of autorotation was encountered The loss of powerfrom one engine was immediately followed by a drop in rotorspeed and increased power demand on the other engine Theengine power and the nozzle setting were controlled with theHarrier system, which has only one engine Limiters in both systemsprotected against overspeed and overtemperature It wasconcluded that a fully redundant system is necessary in thefixed-wing aircraft, while a single system or a system-and-a-halfmay be used in a helicopter due to life-cycle cost considerations

M S K

A83-36314*# United Technologies Corp , East Hartford, ConnIMPORTANCE OF INLET BOUNDARY CONDITIONS FORNUMERICAL SIMULATION OF COMBUSTOR FLOWSG J STURGESS, S A SYED, and K R MCMANUS (UnitedTechnologies Corp, Commercial Engineering Div, East Hartford,CT) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 12 p refs(Contract NAS3-23524)(AIAA PAPER 83-1263)

Fluid dynamic computer codes for the mathematical simulationof problems in gas turbine engine combustion systems are requiredas design and diagnostic tools To eventually achieve aperformance standard with these codes of more than qualitativeaccuracy it is desirable to use benchmark experiments for validationstudies Typical of the fluid dynamic computer codes beingdeveloped for combustor simulations is the TEACH (TeachingElliptic Axisymmetnc Characteristics Heunstically) solutionprocedure It is difficult to find suitable experiments which satisfythe present definition of benchmark quality For the majority ofthe available experiments there is a lack of information concerningthe boundary conditions A standard TEACH-type numericaltechnique is applied to a number of test-case experiments It isfound that numerical simulations of gas turbine combustor-relevantflows can be sensitive to the plane at which the calculations startand the spatial distributions of inlet quantities for swirling flows

GR

A83-36316*# Detroit Diesel Allison, Indianapolis, IndAPPLICATION OF 3D AERODYNAMIC/COMBUSTION MODELTO COMBUSTOR PRIMARY ZONE STUDYR E SULLIVAN, R SUTTON, G MILES, E YOUNG (GeneralMotors Corp, Detroit Diesel Allison Div, Indianapolis, IN), and DBRIEHL (NASA, Lewis Research Center, Cleveland, OH) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 9 p(Contract NAS3-22762)(AIAA PAPER 83-1265)

A description is provided of the three-dimensional elliptic codefor reacting flows used in the combustor design process duringthe program 'Small Gas Turbine Combustor Primary Zone Study'carried out by a U S company The code, designated MARC-I(multidimensional aerodynamic recirculatmg combustion-Version I)is an adaptation of the model described by Mongia et al (1979)The program has the objective to advance the technology of thesmall reverse-flow annular combustor design through anunderstanding of primary zone performance factors The MARC-Icode was used for performance predictions of both original designsand later modifications A test program consisting of both primaryzone sampling and overall combustor performance measurementswas carried out It was, therefore, possible to compare the analyticalpredictions with actual test measurements G R

A83-36322#RESULTS OF TESTS OF A RECTANGULARVECTORING/REVERSING NOZZLE ON AN F100 ENGINEG H MCLAFFERTY and J L PETERSON (United TechnologiesCorp, Pratt and Whitney Group, West Palm Beach, FL) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29,, 1983 8 p(AIAA PAPER 83-1285)

The present investigation is concerned with the results of atest program conducted on an F100 engine in a sea level testfacility The tests take into account all engine/nozzle designoperating modes including steady-state and transient engine andnozzle operation in the forward thrust, vectoring, and reversingmodes throughout the engine power spectrum It was found thatrectangular nozzle configurations can meet future requirementsfor performance and response The two-dimensionalconvergent-divergent nozzle design concept tested showsexceptional potential for continuing development Thrustmanagement through exhaust nozzle thrust spoiling provides a 3Ximprovement in engine transient thrust response Utilizing IRcamera temperature measuring techniques provides an order ofmagnitude improvement in nozzle thermal environment data

GR

A83-36323*# Pratt and Whitney Aircraft Group, East Hartford,ConnEJECTOR NOZZLE TEST RESULTS AT SIMULATED FLIGHTCONDITIONS FOR AN ADVANCED SUPERSONIC TRANSPORTPROPULSION SYSTEMD P NELSON (United Technologies Corp , Pratt and WhitneyGroup, East Hartford, CT) and D L BRESNAHAN (NASA, LewisResearch Center, Cleveland, OH) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 11p refs(AIAA PAPER 83-1287)

Results are presented of wind tunnel tests conducted to verifythe performance improvements of a refined ejector nozzle designfor advanced supersonic transport propulsion systems The analysisof results obtained at simulated engine operating conditions isemphasized Tests were conducted with models of approximately1/1 Oth scale which were configured to simulate nozzle operationat takeoff, subsonic cruise, transonic cruise, and supersonic cruiseTransonic cruise operation was not a consideration during thenozzle design phase, although an evaluation at this condition waslater conducted Test results, characterized by thrust and flowcoefficients, are given for a range of nozzle pressure ratios,emphasizing the thrust performance at the engine operatingconditions predicted for each flight Mach number The results

454


indicate that nozzle performance goals were met or closelyapproximated at takeoff and supersonic cruise, while subsoniccruise performance was within 2 3 percent of the goal with furtherimprovement possible N B

A83-36328#CARS TEMPERATURE AND SPECIES MEASUREMENTS INAUGMENTED JET ENGINE EXHAUSTSA C ECKBRETH, G M DOBBS, J H STUFFLEBEAM (UnitedTechnologies Research Center, East Hartford, CT), and P ATELLEX (United Technologies Corp, Government Products Div,West Palm Beach, FL) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 14 p refs(AIAA PAPER 83-1294)

Coherent anti-Stokes Raman spectroscopy (CARS) is anonmtrusive laser diagnostic technique for spatially- andtemporally-precise measurements of temperature and species inpractical combustion systems Over the last several years, thedevelopment of CARS has progressed from simple flames ofincreasing complexity to practical application in internal combustionengines and simulations of gas turbine combustors Here, the firstapplication of CARS to an actual jet engine is described TheCARS instrument constructed is capable of completely remoteoperation and permits instantaneous thermometry at a 20 Hz rateIts design and operation, as well as sample exhaust measurements,are presented Author

A83-36329#DEVELOPMENT TRENDS IN ENGINE DURABILITYW D COWIE and T A STEIN (USAF, Aeronautical SystemsDiv, Wright-Patterson AFB, OH) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 8 prefs(AIAA PAPER 83-1297)

The Air Force has approximately 38,000 aircraft propulsion unitsin the active inventory A 1977 study reports that over two thirdsof an engine's 15-year life cycle cost is 'ownership costs' andthat the ownership portion is rising It is believed that this situationis driven in large part by modern engines which lack desiredstructural durability In this connection, the Air Force is concernedwith an identification and an understanding of design factors, whichinfluence engine durability It has been found that operationalengines resulting from past development programs have not hadthe durability characteristics necessary for efficient and costeffective operations It is now believed that an organized andsystematic structural development process can help minimizeservice related surprises This realization led to the formulation ofthe Engine Structural Integrity Program (ENSIP) Attention is givento accelerated mission testing, an engine structural maintenanceplan, and an implementation/rationale G R

A83-36340*# Oklahoma State Univ , StillwaterTHE PERFORMANCE OF AN ANNULAR VANE SWIRLERD G LILLEY (Oklahoma State University, Stillwater, OK) and GF SANDER AIAA, SAE, and ASME, Joint Propulsion Conference,19th, Seattle, WA, June 27-29, 1983 14 p USAF-supportedresearch refs(Contract NAS3-74)(AIAA PAPER 83-1326)

In connection with the desirability of optimizing the design of agas turbine combustion chamber, there exists a need for a morecomplete understanding of the fluid dynamics of the flow in suchchambers In order to satisfy this need, experimental and theoreticalresearch is being conducted with the objective to studytwo-dimensional axisymmetric geometries under low speed,nonreactmg, turbulent, swirling flow conditions The flow entersthe test section and proceeds into a larger chamber Inlet swirlvanes are adjustable to a variety of vane angles The presentinvestigation concentrates on the time-mean flow characteristicswhich are generated by the upstream annular swirler Theinvestigation makes use of a five-hole pilot probe technique Atheoretical analysis of swirl numbers associated with severalidealized exit velocity profiles is included, and values of the ratioof maximum swirl velocity to maximum axial velocity at differentswirl strengths are given for each case G R

A83-36346#COMPOUND CYCLE TURBOFAN ENGINEJ G CASTOR (Garrett Turbine Engine Co , Phoenix, AZ) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 9 p(Contract DARPA ORDER 3430, F33657-77-C-0391)(AIAA PAPER 83-1338)

The paper discusses the design and development of criticaltechnologies for a 'near-adiabatic' compound cycle turbofan engine(CCTE) The concept involves replacing the combustor of aconventional turbofan engine with a highly supercharged,high-speed, two-stroke, direct-injected diesel core Primaryemphasis was on reducing specific fuel consumption to improverange x paytoad product Critical diesel core technology areasaddressed were cylinder breathing/scavenging, fuel injection,combustion, materials and lubricants Author

A83-36347#DEVELOPMENT AND APPLICATION OF A LIQUID-COOLED V-8PISTON ENGINE FOR GENERAL AVIATION AIRCRAFTD L BLACKALLER (Thunder Engines, Inc , Van Nuys, CA) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 11 p refs(AIAA PAPER 83-1342)

A83-36339#A JT8D LOW EMISSIONS COMBUSTOR BY RADIAL ZONINGM H ZEISSER and T G FOX (United Technologies Corp, Prattand Whitney Group, East Hartford, CT) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 19838 p refs(AIAA PAPER 83-1324)

A radially zoned, low emissions, can-annular combustionsystem, which has been developed for the JT8D-200 seriesengines, is examined This combustion system utilizes significantlydifferent internal air and fuel flow patterns than previous combustorsand attains very low levels of both emissions and smoke withrelatively simple combustor and fuel injection hardware Theimprovements in performance are accomplished through the useof two distinct concentric combustion zones (radial zoning) whichare formed by controlling airflow and fuel mjector/combustorgeometry A hybrid fuel injector is used to inject the fuel intoeach zone At low power, combustion occurs in the central corezone, while at high power both zones are utilized with the majorityof the fuel being injected into the outer zone N B

A83-36357#ACCELERATED SIMULATED MISSION ENDURANCE TEST OFA TURBOSHAFT ENGINE FOR MILITARY ATTACKHELICOPTER APPLICATIONS P DAVIS (General Electric Co , Aircraft Engine Business Group,Lynn, MA) AIAA, SAE, and ASME, Joint Propulsion Conference,19th, Seattle, WA, June 27-29, 1983 10 p(AIAA PAPER 83-1359)

A test was conceived to subject a factor development testengine to simultaneous vibration and power excursions Duringthe period from March, 1981, through May, 1982, testing wasperformed on a T700-701 turboshaft engine mounted in a factorytest cell The engine and externally mounted airframe hardwarewere from an AH-64A helicopter Attention is given to aspects ofhelicopter simulation, mission simulation, a facility description,details regarding the test method, and the test results It wasfound that the accelerated simulated mission endurance test(ASMET) conducted met the objectives of demonstrating equivalent5000 field mission hour capability of the engine and attachedaircraft components G R

455


A83-36367#KC-135/CFM56 RE-ENGINE - THE BEST SOLUTIONS B KAZIN (General Electric Co, Cincinnati, OH) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 6 p(AIAA PAPER 83-1374)

The KC-135A fleet of tankers was originally established tosupport the bomber force Since that time changes in force structureand basing have greatly increased the need for aerial refuelingAccording to conservative estimates, there is a need for 1200tankers with the capability of the current KC-135A The currentKC-135A inventory is only 642 The least cost method of gainingthe required additional capacity involves an improvement of thecapability of existing aircraft This means that the same numberof aircraft is to be employed, but each aircraft is to be moreeffective As the current engine of the aircraft limits aircraft utility,a new engine, the CFM56, is to be employed Since the enginescomprise the largest flyaway cost element in the KC-135Amodernization program, the program is often referred to as 'TheKC-135 Reengine Program' However, the aircraft will also receiveadditional configuration modifications for enhanced capability

GR

A83-36368#INTRODUCING THE ROLLS-ROYCE TAYP J ASHMOLE (Rolls-Royce, Ltd , East Kilbride, Scotland) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 13 p(AIAA PAPER 83-1377)

This paper covers the background to the launch of theRolls-Royce Tay Turbofan emphasizing the use of a well provencore with the latest fan technology The basic design of the engineis described and the mam performance parameters discussedThis new development provides a thrust increase of the order of25 percent, fuel burn reduction of 15 percent and reduction innoise of the order of 7 PNdB compared with existing Speyinstallations It is therefore an ideal powerplant to providedevelopment potential for existing Spey powered aircraft offeringalso good re-engmmg possibilities on existing airframes Theapplication of this engine to three different aircraft and thesuccessful adoption of a common powerplant is covered, togetherwith a brief review of aircraft performance improvements associatedwith this engine Author

A83-36393*# Tuskegee Inst, AlaA COMPREHENSIVE METHOD FOR PRELIMINARY DESIGNOPTIMIZATION OF AXIAL GAS TURBINE STAGES. II - CODEVERIFICATIONR M JENKINS (Tuskegee Institute, Tuskegee, AL) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 10 p refs(Contract NSG-3295)(AIAA PAPER 83-1403)

The present effort represents an extension of previous workwherein a calculation model for performing rapid pitchlmeoptimization of axial gas turbine geometry, including blade profiles,is developed The model requires no specification of geometricconstraints Output includes aerodynamic performance (adiabaticefficiency), hub-tip flow-path geometry, blade chords, and estimatesof blade shape Presented herein is a verification of theaerodynamic performance portion of the model, whereby detailedturbine test-rig data, including rig geometry, is input to the modelto determine whether tested performance can be predicted Anarray of seven (7) NASA single-stage axial gas turbineconfigurations is investigated, ranging in size from 0 6 kg/s to638 kg/s mass flow and in specific work output from 153 J/g to558 J/g at design (hot) conditions, stage loading factor rangesfrom 1 15 to 4 66 Author

A83-36394#MONTE CARLO SIMULATION OF THE ENGINE DEVELOPMENTPROCESSD G CULY and J J GOSSEN (Garrett Turbine Engine Co ,Phoenix, AZ) AIAA, SAE, and ASME, Joint Propulsion Conference,19th, Seattle, WA, June 27-29, 1983 11 p Navy-sponsoredresearch(AIAA PAPER 83-1405)

The DEVSIM simulation program for generating a Monte Carlosimulation for predicting changes in an engine in its maturedevelopment as a result of unforeseen changes during thedevelopmental process is described The model was formulatedon the bases of a chronological sequence of events and onresource usage The Monte Carlo aspect of the program indicatesif a problem has occurred, identifies the component responsiblefor the problem, and relates the engine maturity to thedevelopmental effort The model accounts for reduced failureincidence for each engine component after redesign Input includesparts costs, test hours and equipment, and the number of enginesput through each type of test A Weibull distribution was employedto describe the lifetime of specific parts DEVSIM was used inconjunction with a life cycle cost model in the cases of a new jetfighter engine at 70 pet of the power and at 70 pet of the scaleof an existing design, and an engine that was a 30 pet derate ofan already-developed engine M S K

A83-36395#THE IMPACT OF ENGINE USAGE ON LIFE CYCLE COSTW S WILLIS and T R SEWALL (General Electric Co, Evendale,OH) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 9 p(AIAA PAPER 83-1406)

The impact of in-service usage of two types of military aircraft,a long-range subsonic bomber and a mixed mission supersonicfighter, on the life-cycle costs (LCC) are evaluated The criticalfactor examined was the time at intermediate power or above,and the total failure rates were projected based on the severity ofthe missions It was found that actual missions in peacetime trainingcan exceed the design expectancies by a factor of two or threeThe LCC analyses were performed with computer programsincluding the operational severity model, the engine acquisitioncost routine, the engine development cost model, an operatingand support cost analysis program, and an LCC summation routineThe tactical system had a more severe service life, although thestresses during training missions mandates that higher fatiguelifetimes be designed into both types of aircraft Componentwear-out was identified as a more important LCC driver than partreliability, and it is suggested that spare engines and modules beprovided to upgrade aircraft availability M S K

A83-36396#LCC EVALUATION OF ADVANCED ENGINE DAMAGETOLERANCE GOALS FOR A HOT-SECTION DISKR J REED, D T HUNTER (United Technologies Corp, Prattand Whitney Group, West Palm Beach, FL), and R J HILL (USAF,Aero Propulsion Laboratory, Wright-Patterson AFB, OH) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 7 p USAF-sponsored research refs(AIAA PAPER 83-1407)

Developments related to Air Force gas turbine engines areconsidered, taking into account the importance of reaching thelowest overall life cycle cost (LCC) by finding an optimumcombination between the high strength capability of a criticalmaterial and its resistance to fatigue crack growth An importantfactor is a component design which includes consideration of crackgrowth characteristics and critical crack size Such a design istermed Damage Tolerant Design (DTD) Attention is given to theresults of a life cycle cost evaluation to quantify the benefits ofdesigning hot-section disks for damage tolerance The workreported was conducted under the Life Cycle Cost/DamageTolerance Assessment program on hot-section damage tolerance,which is currently underway as an evolutionary outgrowth of severalprograms involving the Air Force and a U S aerospace company

456


The guidelines of the Retirement for Cause (RFC) system arealso taken into account G R

A83-36397#ASPECTS OF THE T56 POWER SECTION USAGE/OPERATINGCOSTSC CURRY and J A KORN (General Motors Corp, Detroit DieselAllison Div , Indianapolis, IN) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 6 prefs(AIAA PAPER 83-1408)

The power section of the Detroit Diesel Allison (DDA) T56engine provides a unique opportunity to relate a variety ofapplications to cost of operation Parameters for cyclic and hot-timeusage for both the turboprop and marine/industrial engines arequantitatively deduced and related to unscheduled engine removalsand operating cost It was found that removal frequency of allsystems correlated well with cyclic usage, but had no correlationwith percent hot-time Operating costs also correlated well withcyclic engine usage, and it was found that changes in operationalseverity produced similar changes in operating costs for allsystems Author

A83-36398#DEVELOPMENT OF SIMULATED MISSION ENDURANCE TESTACCELERATION FACTORS IN DETERMINING ENGINECOMPONENT SERVICEABILITY AND FAILURE MODECRITICALITYT R METZ and P J ZIMMERMAN (U S Naval Air PropulsionTest Center, Trenton, NJ) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 6 p(AIAA PAPER 83-1409)

The use of Accelerated Simulated Mission Endurance Testing(ASMET) is a cost effective method of verifying engine durabilityin projected aircraft weapon system application ASMET is a gasturbine engine durability test which simulates the aircraft missionin a test environment A test acceleration methodology has beendeveloped utilizing mission profiles and mission mix to definecomposite profiles which do not lose mission orientation and stillaccelerate the damage processes Identifying the damageprocesses is critical since failure mode damage acceleration rateswill differ with each failure mode These failure mode conditionsare identified from the mission profile/mission mix and retained inthe composite profile, while non-damaging mission aspects aredeleted The composite profiles are then used as the ASMETcycle The ASMET acceleration factors are then determined as aratio of mission profile/mission mix time to test composite time

Author

A83-36400#CONFIGURATION SELECTION AND TECHNOLOGYTRANSITION IN 5000 SHP CLASS ENGINESD D KLASSEN (General Electric Co, Lynn, MA) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 7 p(AIAA PAPER 83-1411)

The basis for the selection of the configuration for the nextgeneration 5000 SHP class engine is presented Analysis of overalladvantages, trade-offs and configurational alternatives werestudied All available technology developments are considered withthe objective of providing the best balance between performance,cost, and the field oriented requirements of reliability, maintainabilityand vulnerability In parallel with the configuration selection,transitioning of new technology from the component stands anddrawing boards is described Component testing was conductedto demonstrate key features, technologies, and designimprovements that were new, an extension of available technology,or an adaptation to engine constraints of features developed ingeneric technology programs with the key objective of reducingrisk to the engine development program The interrelationship ispresented of configuration selection and technology transition toform the best balance of performance, weight, and field

serviceability for the next generation 5000 SHP aircraft engine forthe 1990's Author

A83-36412#FIGHTER ENGINE CYCLE SELECTIONG A PLOURDE, R E SIMS, and R A CEA (United TechnologiesCorp, Pratt and Whitney Group, West Palm Beach, FL) AIAA,SAE, and ASME, Joint Propulsion Conference, 19th, Seattle, WA,June 27-29, 1983 9 p refs(Contract N00019-80-C-0225, F33657-72-C-0242)(AIAA PAPER 83-1300)

The Joint Advanced Fighter Engine (JAFE) DemonstratorProgram approach to accommodating the uncertainty of enginecycle and size requirements is the subject of this paper Data ispresented which shows that while the optimum engine cyclechanges with mission requirements, the penalty associated with anonoptimum engine cycle is small for a large range of cyclevariables This allows for the confident selection of an engine forthe JAFE Program and a future size adaptation through changesprimarily to the low pressure spool Author

A83-36463#PROPULSION PROTOTYPES AT GENERAL ELECTRICT F FOY (General Electric Co , Lynn, MA) IN Aircraft Prototypeand Technology Demonstrator Symposium, Dayton, OH, March23, 24, 1983, Proceedings New York, American Institute ofAeronautics and Astronautics, 1983, p 73-82 10 p(AIAA PAPER 83-1053)

Development histories are presented for proprietary programsof military gas turbine engine development, with comparisons beingconducted to indicate the unique character of each such effortThe engines in question are the YJ101, which served as prototypefor the F404, the F101/DFE, which was the prototype of theF110 engine, the GE12 technology demonstrator for the T700,and the TF34 engine The development programs fall into thecategories of prototype, technology demonstrator and/or full scaledevelopment Attention is given to engine program managementinteraction with airframe development O C

A83-36464#TECHNOLOGY AND ENGINE DEMONSTRATOR PROGRAMSW R ALLEY, JR (United Technologies Corp, GovernmentProducts Div, West Palm Beach, FL) IN Aircraft Prototype andTechnology Demonstrator Symposium, Dayton, OH, March 23, 24,1983, Proceedings New York, American Institute of Aeronauticsand Astronautics, 1983, p 83-87(AIAA PAPER 83-1064)

The paper discusses the merits and complementary aspectsof technology and engine demonstrator programs Technologydemonstrators prove readiness of technology transfer to anoperational system whereas engine demonstrator programs areused to prove system capability for full scale development Bothtypes of programs contribute to new weapon systems Examinationof the F100 demonstrator and Advanced Turbine Engine GasGenerator (ATEGG) programs gives some insight into thecomplementary aspects and payoff for using both types of programsas part of the engine development process Author

A83-36612ADVANCED PROPULSION CONTROLS - A TOTAL SYSTEMVIEWP H YOUNG (Rolls-Royce, Ltd , London, England) AeronauticalJournal (ISSN 0001-9240), vol 87, May 1983, p 165-172

The necessity of designing engine control systems integrallywith the total propulsion control system is explored, with attentiongiven to the effectiveness of electronic control systems The controlsystem links the pilot to the propulsion system, airframe systems,and the cockpit displays The use of electronic controls with theirinherent high defect rates requires built-in test capabilities in orderto assure flight safety as well as the ability to continue to a mainbase for repairs Each function of the digital control system mustbe designed in consideration of its effect on the other functionscontrolled Additionally, safeguards must be included to prohibit

457


the engine from malfunctioning if a pilot command is receivedwhich exceeds the operational envelope Further discussions arepresented on a typical airframe/engine interface, the full authoritywith no mechanical reversion FADEC system, the minimumrequirements of the FADEC system, and system designprinciples M S K

A83-36791#FORCED AND SELF-EXCITED VIBRATIONS OF GAS-TURBINEASSEMBLIES WITH PERFECT AND PERTURBED SYMMETRY[DRGANIA WYMUSZONE I SAMOWZBUDNE PODZESPOLOWTURBINY GAZOWEJ O SCISLEJ I ZABURZONEJ SYMETRII]E STANKIEWICZ Instytut Lotnictwa, Prace (ISSN 0509-6669),no 91, 1982, p 3-27 In Polish

An analysis is presented of the dynamic characteristics ofgas-turbine assemblies possessing axisymmetry, and of the effectof perturbations of this symmetry on the level of forced vibrationsand the possibility of self-excited vibrations Symmetry-group theoryis used in the analysis in view of the importance of the frequencydegeneracy of such vibrations B J

A83-36792#MATHEMATICAL MODELS OF THE ACOUSTIC PROPERTIESOF PROPELLERS [MODELE MATEMATYCZNE WLASCIWOSCIAKUSTYCZNYCH SMIGIEL SAMOLOTOWYCH]A CHYLA Instytut Lotnictwa, Prace (ISSN 0509-6669), no 91,1982, p 29-62 In Polish refs

The features of propeller noise are discussed with referenceto existing airworthiness regulations Various mathematical modelsthat can be used to describe the noise generated by propelleraircraft are examined in detail, and data obtained using thesemodels are compared with experimental data B J

A83-36793#ELECTROHYDRAULIC FUEL-FLOW REGULATOR FORGAS-TURBINE-ENGINE CONTROL SYSTEMS[ELEKTROHYDRAULICZNY STEROWNIK PRZEPLYWU DOUKLADOW REGULACJI SILNIKOW TURBINOWYCH]W BALICKI Instytut Lotnictwa, Prace (ISSN 0509-6669), no 91,1982, p 63-72 In Polish refs

An experimental electrohydraulic fuel-flow control device isdescribed which operates according to the principle of constantpressure head across a metering orifice of variable area Thearea of this orifice is regulated by a mechanism the input quantitiesof which are signals of the position angle of the control lever andof the stagnation pressure of air at the inlet, and the signalgenerated by the electronic unit controlling the driving motor ofthe mechanism The signal of pressure-head variation across themetering orifice produces a variation in the discharge of the pistonpump supplying the control device In the case of manual(emergency) control, the measured flow rate is a function of theposition angle of the control level and the air pressure head Inthe case of automatic control, this flow rate is a function determinedby the operation of the electronic unit and its output signal B J

A83-36912#V/STOL STATUS FROM THE ENGINE TECHNOLOGYVIEWPOINTG M LEWIS and W J LEWIS (Rolls-Royce, Ltd , Bristol,England) Journal of Aircraft (ISSN 0021-8669), vol 20, July1983, p 580-586


A83-36925#AN UPDATE ON HIGH OUTPUT LIGHTWEIGHT DIESELENGINES FOR AIRCRAFT APPLICATIONSM E MOYNIHAN, S G BERENYI, and A P BROUWERS(Teledyne Continental Motors, General Products Div, Muskegon,Ml) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 18 p refs(AIAA PAPER 83-1339)

In connection with fuel-related developments, there is renewedinterest within the aviation industry for new, fuel efficient, multifuel

power plants NASA funded several engine manufacturers toconceptually design new aircraft engines using projected advancedtechnologies One company elected to evaluate the diesel enginecycle with respect to its capability to satisfy a number of specifiedminimum requirements Using past engines as guidelines, anextensive parametric study was made to first determine the basicoverall engine type and next to apply new technologies to achievea truly advanced engine The five engines designs which ultimatelyevolved share a number of common features These features arepartly related to the use of a radial engine configuration, atwo-stroke cycle, a low effective compression ratio, minimumcylinder cooling, a high-pressure fuel injection system, and ahigh-pressure ratio, high efficiency turbocharger Questionsregarding the market acceptance of the diesel engine are alsoexplored G R

N83-25711*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioNASA PROPULSION CONTROLS RESEARCHF TEREN 1983 11 p refs Presented at the 6th InternSymp on Air Breathing Engines, Pans, 6-11 Jun 1983, sponsoredby International Society on Air Breathing Engines and AssociationAeronautique et Astronautique de France(NASA-TM-83343, E-1558, NAS 1 1583343) Avail NTIS HCA02/MF A01 CSCL21E

Multivanable control theory is applied to the design of multipleinput and output engine controls Highly-accurate, real-time enginesimulations are utilized for control development and checkoutElectro-optical control components are developed for use inelectronic control systems having fiber optic data links Integratedcontrols are developed for VSTOL and Rotorcraft propulsionsystems Post-stall models of engine systems are developed toaid in understanding and control of post-stall engine behavior

Author

N83-25712*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioDESIGN ANALYSIS OF A SELF-ACTING SPIRAL-GROOVE RINGSEAL FOR COUNTER-ROTATING SHAFTSE DIRUSSO May 1983 12 p refs(NASA-TP-2142, E-1253, NAS 1 602142) Avail NTIS HCA02/MFA01 CSCL11A

A self-acting spiral groove inter-shaft ring seal of nominal 16 33cm (6 43 in) diameter for sealing fan bleed air betweencounter-rotating hafts in advanced turbofan engines was analyzedThe analysis focused on the lift force characteristics of the spiralgrooves A NASA Lewis developed computer program for predictingthe performance of gas lubricated face seals was used to optimizethe spiral groove geometry to produce maximum lift force Loadcapacity curves (lift force as function of film thickness) weregenerated for four advanced turbofan engine operating conditionsat relative seal speeds ranging from 17,850 to 29,800 rpm, sealedair pressures from 6 to 42 N/sq cm (9 to 60 psi) absolute andtemperatures from 95 deg to 327 C (203 deg to 620 F) Therelative seal sliding speed range was 152 to 255 m/sec (500 to836 ft/sec) The analysis showed that the spiral grooves arecapable of producing sufficient lift force such that the ring sealwill operate in a noncontactmg mode over the operating range oftypical advanced turbofan engines Author

N83-25713# Dayton Univ , Ohio Research InstHIGH FREQUENCY FATIGUE OF TURBINE BLADE MATERIALFinal Technical Report, Oct. 1979 - Jul. 1982R C GOODMAN and A M BROWN Wright-Patterson AFB,Ohio AFWAL Oct 1982 119 p refs(Contract F33615-79-C-5108, AF PROJ 2418)(AD-A124585, UDR-TR-82-104, AFWAL-TR-82-4151) AvailNTIS HC A06/MF A01 CSCL 21E

This increased fatigue crack growth rate at elevated temperaturedue to high frequency loading is examined The crack growth rateis found to depend upon major cycle stress intensity factor,hold-time and minor cycle frequency, and amplitude for a giventemperature The elevated tests also demonstrate a transition from

458


creep crack growth dominant to fatigue crack growth dominant atvalues of minor cycle amplitude above a threshold value A modelfor determining the crack growth rate is developed GRA

N83-25714# RAND Corp , Santa Monica, CalifDEVELOPMENT AND PRODUCTION COST ESTIMATINGRELATIONSHIPS FOR AIRCRAFT TURBINE ENGINES InterimReportJ L BIRKLER, J B GARFINKLE, and K E MARKS Oct 198281 p refs(Contract F49620-82-C-0018)(AD-A123753, RAND/N-1882-AF) Avail NTIS HC A05/MF A01CSCL 05A

This document describes a recent study of cost estimatingrelationships for new military aircraft turbine engine developmentand production programs It presents equations for estimatingdevelopment and production costs and time of arrival for U Smilitary turbojet and turbofan engines The study derives new costestimating relationships from an expanded data base and usesnew diagnostic statistics to screen the relationships and to evaluatethe characteristics of the preferred set Section two of this noteidentifies the data used, explains the criteria and rationale forselecting explanatory variables, and describes recently developedregression diagnostics Section three presents the preferred setof relationships Comments on these results, a comparison withDAPCA equations, suggestions for the use of the cost estimatingrelationships and directions for possible future research arediscussed in Section four Supporting statistics for the predictivemodels are available in the Appendix Author (GRA)

N83-25715# Air Force Systems Command, Wright-Patterson AFB,Ohio Foreign Technology DivGENERALIZATION OF THE AIR-JET PROPULSION SYSTEMS,THE 'N' FLOW TURBO-JET ENGINEV STANCIU 9 Dec 1982 12 p refs Transl into ENGLISHfrom Buletinul Inst Politehnic 'Gheorghe Gheorghiu-Dej' Bucuresti,Ser Mech (Romania), v 43, no 2, 1981 p 77-84(AD-A123932, FTD-ID(RS)T-1561-82) Avail NTIS HC A02/MFA01 CSCL 21E

The possibility of investigating the performance of airspacepropulsion systems on the basis of the characteristics andperformance of a generalized propulsion system is considered withemphasis on the performance of the 'n' flow turbojet engine Outof the analysis of the performance of this engine, the knownsolutions are obtained by participation the turbojet engine withsimple flow, the turbojet engine with turboflow, and theturbopropulsion engine The advantages of using a turbojet enginewith triple flow are considered The generalized turbojet enginehas a specific performance superior -to that of existing engines(higher specific force and lower specific fuel consumption) at thesame frontal section

N83-26791# Air Force Aero Propulsion Lab, Wright-PattersonAFB, Ohio Ramjet Technology BranchCOAXIAL DUMP COMBUSTOR INVESTIGATIONS Final ReportR R CRAIG, J E DREWRY, and F D STULL In AFWAL ACollection of Papers in the Aerospace Sci p 145-156 Jun1982 refsAvail NTIS HC A99/MF A01 CSCL 21E

An experimental investigation was conducted involving coaxialdump combustors with two different types of flameholders (annularand Y) installed at the dump station in an attempt to correlatecombustor performance with previous nonreacting flowfield resultsFlameholder blockage, combustor length, exit area ratio, inlettemperature, and chamber pressure were varied for both wallinjection and premixed fuel conditions Lean blowout limits,combustion efficiency, combustor total pressure drop, and wallstatic pressure distributions were obtained from these runs usingJP-4 fuel In addition, a limited amount of surface heating patternsand combustion oscillation data were obtained Author

N83-26798# Air Force Aero Propulsion Lab, Wright-PattersonAFB, Ohio Turbine Engine DivTHE USE OF VORTEX GENERATORS AS INEXPENSIVECOMPRESSOR CASING TREATMENT Final ReportC H LAW, A J WENNERSTROM, and W A BUZZELL InAFWAL A Collection of Papers in the Aerospace Sci p 358-371Jun 1982 refsAvail NTIS HC A99/MF A01 CSCL 20E

This paper describes an inexpensive form of casing treatmentwhich was found to increase both efficiency and stall margin inan axial compressor stage and which could be easily and cheaplyretrofitted to existing engines The method consists of placementof a row of vortex generators on the outer casing of an axialcompressor, upstream of the rotor Design techniques aredescribed An experimental investigation is also described in whichvortex generator tip treatment was applied to a single stage axialcompressor Gains in compressor and stall margin wereobserved Author

N83-26838*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioDYNAMIC DISTORTION IN A SHORT S-SHAPED SUBSONICDIFFUSER WITH FLOW SEPARATIONR STUMPF, H E NEUMANN, and C C GIAMATI 1983 20 prefs Presented at the 19th Joint Propulsion Conf, Seattle, 27-29Jun 1983, sponsored by AIAA, SAE and ASME(NASA-TM-84312, E-1695, NAS 1 1584312) Avail NTIS HCA02/MF A01 CSCL 21E

An experimental investigation of the time varying distortion atthe diffuser exit of a subscale HiMAT forebody and inlet wasconducted at Mach 0 9 in the Lewis 8 by 6 foot Supersonic WindTunnel A transitory separation was detected within the subsonicdiffuser Vortex generators were installed to eliminate the flowseparation Results from a study of the instantaneous pressurevariations at the diffuser exit are presented The time unsteadytotal pressures at the diffuser exit are computer interpolated andpresented in the form of a movie showing the transitory separationLimited data showing the instantaneous distortion levels is alsopresented Author

N83-26839*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioTHRUST PERFORMANCE OF A VARIABLE-GEOMETRY,DIVERGENT EXHAUST NOZZLE ON A TURBOJET ENGINE ATALTITUDED M STRAIGHT and R R COLLOM Jun 1983 39 p refs(NASA-TP-2171, E-1451, NAS 1602171) Avail NTIS HCA03/MFA01 CSCL 21E

A variable geometry, low aspect ratio, nonaxisymmetric, twodimensional, convergent-divergent exhaust nozzle was tested atsimulated altitude on a turbojet engine to obtain baseline axial,dry thrust performance over wide ranges of operating nozzlepressure ratios, throat areas, and internal expansion area ratiosThe thrust data showed good agreement with theory and scalemodel test results after the data were corrected for seal leakageand coolant losses Wall static pressure profile data were alsoobtained and compared with one dimensional theory and scalemodel data The pressure data indicate greater three dimensionalflow effects in the full scale tests than with models The leakageand coolant penalties were substantial, and the method todetermine them is included Author

N83-26840# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringAPPLICATION OF THE VORTEX-LATTICE METHOD TOPROPELLER PERFORMANCE ANALYSIS M.S. ThesisM I MASQUELIER Jul 1982 115 p refs(AD-A124837, AFIT/GAE/AA/81D-19) Avail NTIS HC A06/MFA01 CSCL 12A

The objective of this thesis is to examine the feasibility ofapplying a vortex lattice method to propeller performance analysisThis method allows the calculation of spanwise and chordwisepressure distributions on thin propeller blades of arbitrary planform

459


The research for this project involves the application of a vortexlattice method to a propeller with twisted, non-cambered, constantchord blades The analysis assumes incompressible, inviscid flowover thin sections The helical wake is modeled as a series ofstraight vortex filament segments A computer code has beendeveloped which uses a vortex lattice method to predictperformance for propellers Results are shown for several operatingconditions, using various angle of attack distributions, numbers ofblades on the propeller, and advance ratios Similar results areshown using the blade-element theory for comparison Resultsindicate that this vortex lattice method is applicable to initialpropeller performance analysis Author (GRA)

N83-26841# Naval Postgraduate School, Monterey, Calif Deptof AeronauticsFINITE ELEMENT PROGRAM FOR CALCULATING FLOWS INTURBOMACHINES WITH RESULTS FOR NASA TASK-1COMPRESSOR M.S. ThesisJ A FERGUSON, III Oct 1982 248 p refs(AD-A124987) Avail NTIS HC A11/MF A01 CSCL 20D

A general mesh generation code (MESHGEN) and finite elementflow solver (TURBO) for calculating the flow development throughaxial turbomachmes are fully documented The finite elementapproach followed Hirsch and Warzee Excellent results wereobtained for the NASA Task-1 compressor operating with subsonicflow conditions Construction of the code will allow straightforwardextension to transonic flows, turbine stages and multiple stagemachines Author (GRA)

08

AIRCRAFT STABILITY AND CONTROL

Includes aircraft handling qualities, piloting, flight controls, andautopilots

A83-33900USING ADAPTIVE CONTROL TO SYNTHESIZE INVARIANT ANDPARTIALLY AUTONOMOUS AUTOMATIC STABILIZATIONSYSTEMSB N PETROV, B V VIKTOROV, F A MIKHAILOV, and V LPOKHVALENSKII Automation and Remote Control (ISSN0005-1179), vol 43, no 11, Apr 20, 1983, pt 2, p 1448-1459Translation refs

A method is developed for increasing the operating accuracyof a multivanable automatic stabilization system, which utilizesspecial compensating signals that adaptively implement thetwo-channel design This adaptive compensation procedure canalso be used to ensure the autonomy of the state vector of somerelevant subsystems when applied to the control of multivanablesystems The operation of this adaptive algorithm only requirescontrolling the forced component of the total motion of the systemand therefore assumes fast decay of the natural modes Thisapproach to the construction of the adaptation procedure is foundto substantially reduce the number of parameters that need to beadjusted The compensation procedure is applied to the automaticangular stabilization of an aircraft in the longitudinal plane Resultsof experimental studies show that these invariance-generatmgmethods are sufficiently effective in practice when real effectordevices are used N B

N83-26842# Rolls-Royce Ltd , Derby (England)METHOD OF STUDYING THE OPERATING TEMPERATURE OFGAS TURBINESY N DOTSENKO and I P PELEPEICHENKO 13 Jul 1982 10p refs Transl into ENGLISH of Samoletostr - Tekh VozdushFlota (USSR), v 45, 1979 p 20-25(PNR-90159, TRANS-15857/TLT-00841) Avail NTIS HCA02/MF A01

A method for obtaining the temperature of gas turbine aircraftengines using two bulb-thermometers with different thermal inertiacharacteristics is presented The thermal balance equations for abulb inside a protective shield are developed Temperature of thegas outside the shield is calculated by allowing for convectiveheat transfer with the gas and radiant heat exchange with theshield, and for the inertia of one of the thermometers Maximumrelative error is 8%, compared with 34% for single thermometermethods Author (ESA)

A83-34854COMPUTER STUDIES OF ACV HEAVE PERFORMANCE AS AFUNCTION OF VENT VALVE CONTROL PARAMETERSJ R AMYOT (National Research Council, Ottawa, Canada) INCanadian Symposium on Air Cushion Technology,' 16th,Charlottetown, Prince Edward Island, Canada, October 19-21, 1982,Preprints Ottawa, Canadian Aeronautics and Space Institute, 1982,p 30-36 refs

A hybrid computer model of the heave dynamics of an aircushion with a segmented skirt and an automatic vent valve controlsystem was used to investigate the effects of control gam andvalve set point variations on the hull's response to step changesin ground level Results have shown that there is an optimumvalue of control gam and the valve set point position can be setto zero to minimize flow power requirements without significantlychanging the dynamical performance Author

N83-26843# Royal Inst of Tech , Stockholm (Sweden) Deptof AeronauticsEXPERIMENTAL STUDY OF STRENGTH AND EXISTANCEDOMAIN OF GROUND-TO-AIR INLET VORTICES BY GROUNDBOARD STATIC PRESSURE MEASUREMENTSS O RIDDER and I SAMUELSSON 1982 27 p refs(PB83-144865, KTH-AERO-TN-62, TRITA-FPT-042) Avail NTISHC A03/MF A01 CSCL 21E

When an air inlet is aspirating in close proximity to the groundplane and the inlet under some flow conditions This vortex couldcause problems with foreign object mgestion that might damagethe bladmg of the engine In this investigation the strength andexistence domain of the inlet vortex has been studied in a lowspeed wind tunnel by measurements of the ground plane timeaverage static pressure below the inlet GRA

A83-35121#APPLICATION OF MAXIMUM LIKELIHOOD ESTIMATION TOTHE IDENTIFICATION OF THE STABILITY DERIVATIVES OF AWIDE BODY TRANSPORT AIRCRAFTK M SOBEL and E Y SHAPIRO (Lockheed-California Co ,Burbank, CA) IN Annual Allerton Conference on Communication,Control, and Computing, 19th, Monticello, IL, September30-October 2, 1981, Proceedings Urbana, IL, University of Illinois,1982, p 339-347 refs

Maximum likelihood estimation is applied to data obtained froma simulation of the lateral dynamics of an L-1011 aircraft at acruise flight condition The model includes a stability augmentationsystem (SAS), actuator dynamics, sensor noise, and random gusteffects The relative importance of the various stabilnty derivativesand the results of the identification procedure are discussed

Author

460

08 AIRCRAFT STABILITY AND CONTROL

A83-35773#AIRCRAFT ACTIVE CONTROLS • NEW ERA IN DESIGNC HWANG and D F KESLER (Northrop Corp, Aircraft Div,Hawthorne, CA) Astronautics and Aeronautics (ISSN 0004-6213),vol 21, June 1983, p 70-79, 85 refs

The control systems of the modern aircraft accept, in additionto pilot's commands, also sensor information reflecting flightcondition and dynamic response The response may includerigid-body rates, accelerations, and control-surface positionsSensor information feeds back through a number of networks toeffect positive control This 'active control' of structural dynamicbehavior and its effect upon the flight-control system has beenrelatively new to the structural community In connection with theseand other modern developments, many new requirements are beingimposed upon aircraft control-system designers An overview isprovided concerning the new developments affecting aircraftcontrol-system design Attention is given to a classification ofactive-control systems, a flutter-suppression model, a Nyquistanalysis for a forward-swept-wmg aircraft, the organization of adigital adaptive control system, the integration of active controlinto the flight control system, and a wing load alleviation system

GR

N83-25716# Naval Air Development Center, Warminster, PaAircraft and Crew Systems Technology DirectorateA PRELIMINARY ASSESSMENT OF HELICOPTER/VSTOLHANDLING QUALITIES SPECIFICATIONSK GOLDSTEIN 4 Nov 1982 120 p refs(Contract WF41400000)(AD-A124667, NADC-81023-60) Avail NTIS HC A06/MF A01CSCL 01C

The flying quality characteristics of four state-of-the-art rotarywing aircraft have been compared to the present day helicopterand VSTOL flying qualities criteria Hover control power anddynamic stability characteristics were analyzed for the longitudinal,lateral and directional axes For forward flight, static and dynamicstability characteristics were analyzed for the longitudinal andlateral-directional axes Results in terms of the applicability/utilityof the MIL-H-8501A criteria are presented for each of the aboveflying qualities areas Author (GRA)

N83-25717# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringINVESTIGATION OF AN IMPROVED FINITE ELEMENT MODELFOR A REPAIRED T-38 HORIZONTAL STABILIZER FLUTTERANALYSIS USING NASTRAN M S. ThesisG G LONDON, JR Dec 1982 47 p refs(AD-A124741, AFIT/GAE/AA/82D-19) Avail NTIS HC A03/MFA01 CSCL 20D

This thesis investigated the use of an improved finite elementmodel of a T-38 horizontal stabilizer for flutter analysis usingNASTRAN The procedure for evaluating the effect of repairs onthe flutter speed is developed and its sensitivity to several modelingassumptions and practices is presented The procedure is to beused by Air Force engineers to evaluate repair limits of T-38 stabsThe results show that the current repair limits have little or noeffects on the flutter conditions, therefore, the procedurespresented in this investigation should be used to establish newrepair limitations GRA

N83-25718# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringGUST RESPONSE PREDICTION OF AN AIRFOIL USING AMODIFIED VON KARMAN-POHLHAUSEN TECHNIQUE M.S.ThesisR G DOCKEN, JR Dec 1982 81 p refs(AD-A124716, AFIT/GAE/AA/82D-9) Avail NTIS HC A05/MFA01 CSCL 20D

An analytical study is presented regarding the theoreticalbehavior of an airfoil in a pitching airflow The theoreticaldevelopment includes the momentum-integral equation forboundary layers in unsteady flow and the von Karman-Pohlhausenintegral method for unsteady flow A computer program was written

to model this and was applied to a symmetric Joukowski airfoilThe results of this study show a linear relationship between theincrease in the stall angle of attack and the non-dimensional pitchrate GRA

N83-25719# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringFLUTTER PREDICTION IN FORWARD-SWEPT WINGS BYASSUMED MODES AND STRIP THEORY M S ThesisW I SHELTON, JR Dec 1982 59 p refs(AD-A124715, AFIT/GAE/AA/82D-27) Avail NTIS HC A04/MFA01 CSCL 01A

The roots are then plotted and the flutter or divergence speedsdetermined It was found that flutter speed increased anddivergence speed decreased with increasing forward sweep asexpected Also, quasi-steady aerodynamics do not accuratelypredict flutter and the approximation to unsteady aerodynamicsdoes not accurately predict divergence It is necessary to combinethese two methods in order to obtain a complete analysis of thewing's aeroelastic instabilities GRA

N83-26844*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaDETERMINATION OF STABILITY AND CONTROLPARAMETERS OF A GENERAL AVIATION AIRPLANE FROMFLIGHT DATAI ABBASY Mar 1983 45 p refs(NASA-TM-84635, NAS 1 1584635) Avail NTIS HC A03/MFA01 CSCL 01C

Values for the stability and control parameters for a generalaviation airplane were determined from flight data Lateral andlongitudinal transient maneuvers were analyzed by the equationerror and output error methods There was a good agreementbetween the parameters extracted from flight data and thosepredicted by wind tunnel Author

N83-26845*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifA FLIGHT-TEST AND SIMULATION EVALUATION OF THELONGITUDINAL FINAL APPROACH AND LANDINGPERFORMANCE OF AN AUTOMATIC SYSTEM FOR A LIGHTWING LOADING STOL AIRCRAFTS C BROWN, G H HARDY, and W S HINDSON Jun 198359 p refs(NASA-TM-84270, A-8993, NAS 1 1584270) Avail NTIS HCA04/MF A01 CSCL 01C

As part of a comprehensive flight-test program of STOLoperating systems for the terminal area, an automatic landingsystem was developed and evaluated for a light wing loadingturboprop aircraft The aircraft utilized an onboard advanced digitalavionics system Flight tests were conducted at a facility thatincluded a STOL runway site with a microwave landing systemLongitudinal flight-test results were presented and compared withavailable (basically CTOL) criteria These comparisons wereaugmented by results from a comprehensive simulation of thecontrolled aircraft which included representations of navigationerrors that were encountered in flight and atmosphericdisturbances Acceptable performance on final approach and attouchdown was achieved by the autoland (automatic landing)system for the moderate winds and turbulence conditionsencountered in flight However, some touchdown performancegoals were marginally achieved, and simulation results suggestedthat difficulties could be encountered in the presence of moreextreme atmospheric conditions Suggestions were made forimproving performance under those more extreme conditions

Author

461

08 AIRCRAFT STABILITY AND CONTROL

N83-26846*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifPILOT HUMAN FACTORS IN STALL/SPIN ACCIDENTS OFSUPERSONIC FIGHTER AIRCRAFTS B ANDERSON, E K ENEVOLDSON, and L T NGUYEN May1983 12 p refs Presented at the AGARD Conf Flight MechSys Design Lessons from Operational Exper, Athens, 10-13 May1983(NASA-TM-84348, A-9297, NAS 1 1584348) Avail NTIS HCA02/MF A01 CSCL 01C

A study has been made of pilot human factors related tostall/spin accidents of supersonic fighter aircraft The militaryspecifications for flight at high angles of attack are examinedSeveral pilot human factors problems related to stall/spin arediscussed These problems include (1) unsatisfactory nonvisualwarning cues, (2) the inability of the pilot to quickly determine ifthe aircraft is spinning out of control, or to recognize the type ofspin, (3) the inability of the pilot to decide on and implement thecorrect spin recovery technique, (4) the inability of the pilot tomove, caused by high angular rotation, and (5) the tendency ofpilots to wait too long in deciding to abandon the irrecoverableaircraft Psycho-physiological phenomena influencing pilot'sbehavior in stall/spin situations include (1) channelization ofsensory inputs, (2) limitations in precisely controlling severalmuscular inputs, (3) inaccurate judgment of elapsed time, and (4)disorientation of vestibulo-ocular inputs Results are given of pilotresponses to all these problems in the F14A, E.16/AB, and F/A-18Aaircraft The use of departure spin resistance and automatic spinprevention systems incorporated on recent supersonic fighters arediscussed These systems should help to improve the stall/spinaccident record with some compromise in maneuverability

Author

N83-26847# Federal Aviation Agency, Atlantic City, N JDIGITAL FLIGHT CONTROL SYSTEM VALIDATIOND ELDREDGE, J E REED, E HITT (Battelle Columbus Labs,Ohio), J WEBB (Battelle Columbus Labs , Ohio), and D MULCARE(Lockheed-Georgia Co) Jun 1982 19 p refs Presented atthe 1982 Am Control Conf, Arlington, Va , Jun 1982(AD-A124506, FAA-CT-82-54) Avail NTIS HC A02/MF A01CSCL 01C

The introduction of advanced technologies, new designconcepts, and sophisticated high integrity integratedsoftware-based digital flight control and avionics systems hasconfronted the FAA with the task of reviewing, revising, andupdating its airworthiness assessment criteria in these areas TheFAA needs to establish and maintain systems engineering expertiseas well as a capability to establish/evaluate validation/verificationprocedures for software-based digital systems In order toaccomplish this objective, the FAA must have expertise infault-insertion techniques, emulation, automated reliability analyses,failure modes and effects analyses, fault-tree graphics, and otheranalytical tools In addition, these skills are needed in order tointerpret and evaluate data and information submitted, during thecertification, process, in compliance with RTCA DO-178 and FAAAdvisory Circular 251309-XX This paper discusses techniques,methodologies, data, and information required for digital flightcontrol and avionics systems validation Author (GRA)

N83-26848# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringHIGH-GAIN ERROR ACTUATED FLIGHT CONTROL SYSTEMSFOR CONTINUOUS LINEAR MULTIVARIABLE PLANTS M.S.ThesisL THOMAS Dec 1982 151 p refs(AD-A124871, AFIT/GAE/EE/82D-1) Avail NTIS HC A08/MFA01 CSCL 01C

The theory of high-gam error actuated feedback control,developed by Porter and Bradshaw, is applied to the design ofvarious lateral-directional decoupling flight control systems for anadvanced aircraft The controllers developed in this report utilizeoutput feedback with proportional plus integral control to producedesirable closed-loop responses with minimal interactions between

outputs Because of the structure of the system, measurementvariables in addition to the outputs are necessary to apply thismethod The report examines controller design robustness byvarying the flight conditions or maneuver commands from the onesthe controller is specifically designed for, and then judges systemperformance The results show that the controller is robust withrespect to varying flight conditions, but is not robust with respectto varying maneuver commands This report also examines theeffect of first-order actuator dynamics in the system model Actuatordynamics are shown to significantly effect the control systemresponse, indicating that a simplified model, without actuators, isnot desireable in one's control design scheme Also a computerprogram to determine transmission zeros and decoupling zeros isdeveloped Author (GRA)

09

RESEARCH AND SUPPORT FACILITIES (AIR)

Includes airports,,hangars and runways, aircraft repair and overhaulfacilities, wind tunnels, shock tube facilities, and engine testblocks

A83-34429AN ALGORITHM OF FLIGHT SIMULATION ON A DYNAMICSTAND OF SUPPORT TYPE [ALGORITM IMITATSII POLETANA DINAMICHESKOM STENDE OPORNOGO TIPA]V V ALEKSANDROV, I V DYLEVSKII, V D ZIMENKOV, I GTIKHANINA, and O D CHUGUNOV Akademna Nauk SSSR,Izvestua, Mekhanika Tverdogo Tela (ISSN 0572-3299), Mar-Apr1983, p 30-37 In Russian refs

The problem of flight simulation is formulated for an operatorin the cockpit of a dynamic simulator A composition method forsolving this problem is proposed for a stand of support type withsix degrees of freedom, and an algorithm implementing this methodis described As an example, consideration is given to a digitalsystem for the control of a dynamic simulator, and a block diagramof this system is presented It is noted that the simulation dependssignificantly on the kinematic scheme of the stand B J

A83-35598AISA - PROGRAM FOR AUTOMATED TREATMENT OFAERONAUTICAL DATA [AISA - PROGRAMME DE TRAITEMENTAUTOMATISEDE ÎNFORMATION AERONAUTIQUE]A LANGRAND (Direction Generale al'Aviation Civile, Service de('Information Aeronautique, Athis Mons, Essonne, France)Navigation (Pans) (ISSN 0028-1530), vol 31, April 1983, p 162-171In French

The French automated aircraft information service (AISA)capabilities, equipment, and products are described The systemprovides on-line access to a computer which holds notices toairmen, cartographic information, and cargo information Thecartographies subsection provides automated map generation ofaeronautical maps for pilot use The maps can be dimensioned torequest, identify air routes, ground waypomts and landmarks, holdboth typography and graphics and approach paths, and beamenable to interactive processing Notices to airmen aredispatched by teletype, through hard copy printed with a daisywheel, or by transmission to a CRT display in the cockpit Weeklynotices can also be issued and stored for inquiry Finally, thecontract subroutine contains samples of up to 7000 bills of lading,procedures for contracting services, postal rates, etc, as well asdaily shipment records The system will eventually be modified toallow interrogation/response from external consoles M S K

462

09 RESEARCH AND SUPPORT FACILITIES (AIR)

A83-35625U.S. SETS OWN STANDARDS FOR AIRPORT LIGHTINGA C SCHWARTZ Airport Forum (ISSN 0002-2802), vol 13,April 1983, p 65, 67-69

FAA regulations, the types of equipment, and the acceptanceprocedures for airport runway lighting systems are outlinedAlthough several types of equipment installed on federallycontrolled runways are specified precisely with regards materialsand dimensions, local airports are generally permitted to useequipment of their own choice so long as performancespecifications are met Advisory circulars are distributed by theFAA to provide installers of runway lighting equipment with guidesas to spacing, radio control, operation, and maintenanceAdditionally, the FAA issues a list of U S manufactured equipmentwhich it certifies as meeting performance specifications, althoughit is noted that FAA officials attend only 15-20 pet of the actualtests of the equipment by manufacturers M S K

A83-35850#PROPULSION SYSTEM SIMULATION TECHNIQUE FOR SCALEDWIND TUNNEL MODEL TESTINGC C CASSMEYER (McDonnell Aircraft Co, St Louis, MO) INInternational Symposium on Air Breathing Engines, 6th, Paris,France, June 6-10, 1983, Symposium Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 416-421 refs

Propulsion simulators have been developed which allowpropulsion system and airframe flowfields to be simultaneouslysimulated in a single wind tunnel model, thereby improving theaccuracy of aircraft performance prediction It is observed thatthe most effective use of such propulsion simulator-equippedmodels will be on configurations having highly integrated andclosely coupled propulsion systems The matching of the maximumpropulsion simulator airflow with the maximum engine airflow isfound to generally result in an 8-11 percent-scale model Testingwith such models should not be used in an aircraft developmentcycle prior to the selection of such fundamental design featuresas engine cycle, airframe configuration, and propulsion systemintegration O C

A83-35863#GROUND SIMULATION OF ENGINE OPERATION ATALTITUDEB A REESE (Arnold Engineering Development Center, Arnold AirForce Station, TN) IN International Symposium on Air BreathingEngines, 6th, Paris, France, June 6-10, 1983, Symposium Papers


A discussion is presented concerning the contributionsobtainable through ground-simulated high altitude testing of turbojetand turbofan aircraft engine operation, with attention to such criteriafor test program success as the early involvement of test personnelin the engine development process, the justification of groundtesting over flight testing, and adequate funding of the groundtest effort Development status reports are given for theAeropropulsion System Test Facility, which will begin its check-outoperations in the Fall of 1984, and the Turbine Engine LoadSimulator which has not yet received funding Detailed descriptionsare given of the experimental facilities covered O C

A83-36073ALL WEATHER HELIPORTS AND AIRWAY SYSTEM - THEFUTURE NEEDW F PAUL (United Technologies Corp , Sikorsky Aircraft, Stratford,CT) Vertiflite (ISSN 0042-4455), vol 29, Mar-Apr 1983, p16-21

A plan for the development of a national system of heliportsand helicopter airways to accommodate the growth foreseen inthe U S civil helicopter fleet by 1990 is discussed The elementsof the proposed system include allweather heliports located nearthe center of cities, realistic acoustic guidelines, noninterfenngairways for helicopter use only, a navigation, communication, andair-traffic-control network based on NAVSTAR or a similar satellitesystem, improved forecasting of icing and thunderstorm conditions,

helicopters capable of precision steep instrument approaches andtakeoffs at very low speeds, and advanced ice protection for blades,windshields, and propulsion systems The strategy being pursuedby the HAI Heliports and Airways Committee for the implementationof this plan is reviewed T K

A83-36216#SIMULATOR PERFORMANCE DEFINITION BY CUESYNCHRONIZATION ANALYSISS K BUTRIMAS and G B BROWDER (U S Navy, Naval TrainingEquipment Center, Orlando, FL) IN Flight Simulation TechnologiesConference, Niagara Falls, NY, June 13-15, 1983, Collection ofTechnical Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 114-122(AIAA PAPER 83-1092)

This paper describes by experimental example how a cuesynchronization study should be performed on a major flightsimulator system It presents dynamic performance measurementsmade at the Navy's Visual Technology Research Simulator (VTRS)facility, and shows timing interactions between critical subsystemsof the Conventional Takeoff and Landing (CTOL) simulator Itdiscusses how and why specifications and tests must be developedwhich determine the cue synchronization and performancerequirements for simulation systems Author

A83-36217#REAL TIME SIMULATION OF MISSION ENVIRONMENTS FORAVIONICS SYSTEMS INTEGRATIONR A WEEKS (Northrop Corp, Pico Rivera, CA) IN FlightSimulation Technologies Conference, Niagara Falls, NY, June13-15, 1983, Collection of Technical Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 123-129(AIAA PAPER 83-1097)

This paper describes a real time simulation of missionenvironments for use in developing, synthesizing and analyzingcomplex avionics systems for fighter aircraft The problem is oneof creating an operationally correct environment for a pilot tooperate in such that he is properly task loaded Proper task loadinginsures the proper integration of the avionics subsystems (on anoperation level) so as to verify that the mission objectives will befulfilled Author

A83-36218*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifTHE MAN-VEHICLE SYSTEMS RESEARCH FACILITY - A NEWNASA AERONAUTICAL R & D FACILITYD C NAGEL and R J SHINER (NASA, Ames Research Center,Man-Vehicle Systems Research Div , Moffett Field, CA) IN FlightSimulation Technologies Conference, Niagara Falls, NY, June13-15, 1983, Collection of Technical Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 130-139(AIAA PAPER 83-1098)

A new flight simulation facility neanng completion at the NASAAmes Research Center is described The facility is intended tosupport aeronautical human factors research and consists of anew building, two full mission flight simulators and an air trafficcontrol simulator Special features of the new facility are describedwhich make it particularly well suited for human factors research

Author

A83-36219#DATA BASE CONSIDERATIONS FOR A TACTICALENVIRONMENT SIMULATIONC G HORATTAS and R P ADKINS (Goodyear Aerospace Corp ,Akron, Oh) IN Flight Simulation Technologies Conference, NiagaraFalls, NY, June 13-15, 1983, Collection of Technical PapersNew York, American Institute of Aeronautics and Astronautics,1983, p 140-145 refs(AIAA PAPER 83-1099)

This paper discusses data base requirements for simulatingthe sensor environment used in typical military aircraft Certainmission characteristics can be capitalized upon to effect somerelief in the enormous demand on the data base coverage and

463

09 RESEARCH AND SUPPORT FACILITIES

detail, while maintaining the high degree of realism and fidelityneeded to provide adequate training Author

A83-36222*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifCOMPENSATION FOR TIME DELAY IN FLIGHT SIMULATORVISUAL-DISPLAY SYSTEMSD F CRANE (NASA, Ames Research Center, Moffett Field, CA)IN Flight Simulation Technologies Conference, Niagara Falls, NY,June 13-15, 1983, Collection of Technical Papers New York,American Institute of Aeronautics and Astronautics, 1983, p163-171 refs(AIAA PAPER 83-1080)

A piloted aircraft can be viewed as a closed-loop, man-machinecontrol system When a simulator pilot is performing a precisionmaneuver, a delay in the visual display of aircraft response topilot-control input decreases the stability of the pilot-aircraft systemThe less stable system is more difficult to control precisely Pilotdynamic response and performance change as the pilot attemptsto compensate for the decrease in system stability, and thesechanges bias the simulation results by influencing the pilot's ratingof the handling qualities of the simulated aircraft Delaycompensation, designed to restore pilot-aircraft system stability,was evaluated in several studies which are reported here Thestudies range from single-axis, tracking-task experiments (withsufficient subjects and trials to establish statistical significance ofthe results) to a brief evaluation of compensation of acomputer-generated-imagery (CGI) visual display system in a fullsix-degree-of-freedom simulation The compensation was effective- improvements in pilot performance and workload or aircrafthandling-qualities rating (HQR) were observed Results from recentaircraft handling-qualities research literature which support thecompensation design approach are also reviewed Author

A83-36224#VISUALLY-COUPLED SYSTEMS AS SIMULATION DEVICESM W HAAS (USAF, Aerospace Medical Research Laboratory,Wright-Patterson AFB, OH) American Institute of Aeronauticsand Astronautics, Flight Simulation Technologies Conference,Niagara Falls, NY, June 13-15, 1983 5 p(AIAA 83-1083)

It is pointed out that the technology development ofvisually-coupled systems (VCS) began in 1966 VCS provide away to improve weapon aiming accuracy and efficiency whileenlarging the operational delivery envelope of the weapon systemA VCS may derive control information from the operator and directthe weapon system, while simultaneously displaying weapon systeminformation to the operator Control information is derived by ahelmet-mounted sight and/or helmet-mounted oculometerFeedback information is provided by the helmet-mounted displayThe combination of the considered components is termed'visually-coupled system' VCS technologies can also be used toprovide low-cost visual systems for simulators, support researchregarding critical issues of cockpit control, and display design andproper use of VCS components in the airborne environment TheVisually-Coupled Airborne System Simulator was developed tostudy the utilization of the VCS in the simulator G R

A83-36353*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioNASA LOW-SPEED CENTRIFUGAL COMPRESSOR FORFUNDAMENTAL RESEARCHJ R WOOD, P W ADAM, and A E BUGGELE (NASA, LewisResearch Center, Cleveland, OH) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 12p refs(AIAA PAPER 83-1351)

A new centrifugal compressor facility being built by the NASALewis Research Center is described, its purpose is to obtain'benchmark' experimental data for internal flow code verificationand modeling The facility will be heavily instrumented with standardpressure and temperature probes and have provisions for flowvisualization and laser Doppler velocimetry The facility will

accommodate rotational speeds to 2400 rpm and will be rated atpressures to 1 25 atm The initial compressor stage for testing isgeometrically and dynamically representative of modernhigh-performance stages with the exception of Mach number levelsDesign exit tip speed for the initial stage is 500 ft/sec with apressure ratio of 1 17 The rotor exit backsweep is 55 deg fromradial The facility is expected to be operational in the first half of1985 Author

A83-36356#PERFORMANCE CAPABILITY OF A COMPACT MULTIMISSIONAIRCRAFT PROPULSION SIMULATORC D WAGENKNECHT, C J DUSA (General Electric Co,Cincinnati, OH), and T J NORBUT (USAF, Wright AeronauticalLaboratories, Wright-Patterson AFB, OH) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 198310 p refs(AIAA PAPER 83-1358)

The Compact Multimission Aircraft Propulsion Simulator is aflexible cycle miniature turbine engine powered by an externalsource of high pressure air Its development has been to enhancethe propulsion flowfield simulation capability during wind tunneltesting of subscale aircraft models Currently, a data base on theutility of the simulator is being accumulated, however, it will besometime before the complete capability of the simulator andparametric impact of significant variables will be fully characterizedIn the interim, analysis results based on a cycle deck computermodel are presented to parametrically define performance flexibilitycharacteristics which will be a necessary consideration for anypotential simulator user Author

A83-36421#SURVEY OF THE ONERA ACTIVITIES ON THE ADAPTIVE WALLAPPLICATIONS AND COMMUTATION OF RESIDUALCORRECTIONSJ P CHEVALLIER (ONERA, Chatillon-sous-Bagneux,Hauts-de-Seine, France) (Wind Tunnel WallInterference-Assessment/Correction Workshop, NASA, LangleyResearch Center, Hampton, VA, Jan 25, 26, 1983) ONERA, TP,no 1983-11, 1983, 15 p refs(ONERA, TP NO 1983-11)

ONERA activities in the area of computing or reducing windtunnel wall interferences are reviewed, emphasizing improvementin the determination of corrections and the use of adapted flexiblewalls Corrections computed from wall measured data arepresented for the two- and three-dimensional cases, and theoreticaland experimental assessments of the model representation fromthe transverse speed component at the wall and from wall pressuremeasurements, respectively, are given The ONERAtwo-dimensional T2 wind tunnel operation is described, and theiterative process used to adapt the wall is outlined The validationof the adaptive wall operation is addressed Finally, some generalobservations regarding the orientation of the work for the plannedthree-dimensional model are formulated C D

A83-36433#NEW TRANSFORMATIONS OF S4 MODANE HYPERSONICWIND TUNNEL FOR RAMJET MISSILES TESTSJ CHRISTOPHE (ONERA, Chatillon-sous-Bagneux,Hauts-de-Seine, France) (Supersonic Tunnel Association,Semi-Annual Meeting, 59th, Colorado Springs, CO, Apr 6, 7, 1983)ONERA, TP, no 1983-24, 1983, 14 p refs(ONERA, TP NO 1983-24)

The capabilities, equipment, and performance of the ModaneS4 hypersonic wind tunnel are described The tunnel has a Mach6 nozzle, storage facilities for dry air at 400 bars, a heater bed ofaluminum pebbles capable of raising the air temperature to 1850K, and a mounting table with two degrees of freedom Tests canbe run on aerodynamics, air intakes, ablation or radomedeformation, heat transfer, and the performance of completeengines at Mach 6 Full engine trials have included solid fueledramjets, with adaptations permitting connected pipe and semi-freejet testing in conjunction with the hot gas generator The ramjet


trials have been limited to a simulation of Mach 2 7 at groundlevel conditions and Mach 3 35 at altitudes over 11 km M S K

N83-25720# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt, Goettmgen (West Germany) Inst forExperimental Fluid MechanicsCONDENSATION STUDIES IN CRYOGENIC NITROGENEXPANSIONSM DUEKER 1982 14 p Presented at the ETW CryogenicTechno! Review Meeting, Amsterdam, 15-17 Sep 1982Avail NTIS HC A02/MF A01

The Reynolds number range of wind tunnels is extended tohigher values, when the wind tunnel operates under cryogenicconditions With a stagnation temperature, however, chosen toolow, the gas may expand into its liquid or solid phase region,which will cause condensation effects Avoiding impurities in thestreaming medium, heterogeneous condensation is prevented, butin an isentropic expansion, far enough into the liquid or solidphase region, homogeneous condensation will occur Thedetermination of condensation onset points in isentropic expansionsaround realistic airfoils is tested in the European Tronssonic WindTunnel (ETW) Real gas effects in cryogenic flows are notdescribed Author

N83-25721# Oxford Univ (England)TEMPERATURE RESPONSE OF A MODEL TO SET-POINTCHANGES AND CONDITIONING IN ETWW B BALD 1982 28 p refs Presented at the ETWCryogenic Review Meeting, Amsterdam, 15-17 Sep 1982Avail NTIS HC A03/MF A01

Preliminary finite element thermal analysis of a model balancesting arrangement mounted in a cryogenic wind tunnel concludedthat heated balances were unacceptable if the model surfacetemperature was to satisfy the 1% adiabatic wall temperaturecondition specified by Green The results of a more detailed finiteelement thermal analysis on an assumed 0 6 meter long stainlesssteel delta wing model supported by an unheated balance stingarrangement and subjected to the ETW set-point changes andtemperature conditioning specified are summarized Author

N83-25723# Institut de Mecanique des Fluides de Lille(France)MATERIALS AND MODELLING TECHNOLOGY FORCRYOGENIC ENVIRONMENTJ L PETITNIOT and F DUPRIEZ 1982 41 p refsAvail NTIS HC A03/MF A01

Construction of a model and its support for use in a cryogenicwind tunnel induces the following problems relative to the choiceof materials for the different model parts, lifting areas, fuselage,balance, sting line, construction techniques depending on the aimof the tests to be done, joints between model and its support,joints between model support and wind tunnel structure, andisolated or non-isolated board instrumentation According to typeof tests, solicitations on the model in the test section will be veryvariable For static tests, aimed at the determination of aerodynamiccoefficients, maximum stress levels were fixed, with the agreementof air frame designers, to 400 MPa for civil and 800 MPa forfighter models A dynamic stress is added to the static one whosevalue is of the order of 20% of the static stress The frequencyrange lies beyond 30 to 50 Hz As an example for a Mirage delta2000 classic 1/8 scale model, first wing flexure mode is about100 Hz At this level, the balance stiffness effect becomespreponderant and the first frequencies met in wind tunnel arethose of the rigid modes of the model on its support Author

N83-25725# Office National d'Etudes et de RecherchesAerospatiales, Toulouse (France) Aerothermodynamics DeptPROBLEMS INVOLVED BY THE INSTRUMENTATION AND THECONCEPTION OF CRYOGENIC TESTSA BLANCHARD and A MIGNOSI 1982 14 p refs Presentedat the ETW Cryogenic Technol Rev Meeting, Amsterdam, 15-17Sep 1982Avail NTIS HC A02/MF A01

The studies carried out on stall pressure transducers tested atcool temperature, and the development of a probe which wasused in T'3 (a small cryogenic transonic wind tunnel driven with afan) are presented An important point concerns the precoolmg ofthe model, which is necessary in order to obtain a temperatureratio Tw/Taw near 1 during a run (20 to 40 seconds) Thisprecoolmg is planned to be performed in a cooling box besidethe test section, therefore, the model is introduced during the runstarting process To distinguish the effects due to the increase ofReynolds number, from those of specious conditions, the influenceof various parameters must be discerned S L

N83-25726# Royal Aircraft Establishment, Bedford (England)EARLY EXPERIENCE IN USING THE CRYOGENIC TESTFACILITY AT RAE BEDFORD, ENGLANDR D LAW 1982 14 p Presented at the ETW CryogenicTechnol Rev Meeting, Amsterdam, Sep 1982Avail NTIS HC A02/MF A01

A closed circuit test duct has been constructed at RAE Bedfordas part of the United Kingdom support for the ETW programmeThe maximum gas velocity through the 0 3 m square test sectionis 25 m/sec, falling with temperature, and the gas temperaturecan be rapidly reduced and controlled at any level between ambientand 90 K by evaporation of liquid nitrogen A simple calibrationdevice is provided for loading small wind tunnel balances mountedin the test duct and some observations have been made of thebehavior of a 3-component balance under transient temperatureconditions Author

N83-25727*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaMODEL MOUNT SYSTEM FOR TESTING FLUTTER PatentApplicationM G FARMER, inventor (to NASA) 31 Mar 1983 15 p(NASA-CASE-LAR-12950-1, US-PATENT-APPL-SN-481106)Avail NTIS HC A02/MF A01 CSCL 14B

A wind tunnel model mount system is described for effectivelyand accurately determining the effects of angle of attack andairstream velocity on a model airfoil or aircraft The model mountsystem includes a rigid model attached to a splitter plate which issupported away from the wind tunnel wall by a plurality of flexiblerods Conventional instrumentation is employed to effect modelrotation through turntable and to record model flutter data as afunction of the angle of attack versus dynamic pressure NASA

N83-25728# Federal Aviation Administration, Washington, D CRUNWAY SURFACE CONDITION SENSOR SPECIFICATIONGUIDE22 Apr 1983 15 p(AC-150/5220-13A) Avail NTIS HC A02/MF A01

Ice begins to form on pavements when the pavement surfaceis at the freezing temperature of the water solution on it Remoterunway surface condition sensors which will predict and detectthe formation of ice on airport pavements will enhance runwaysafety while reducing airport equipment, manpower, and chemicalcosts The use of air temperatures exclusively to predict theoccurrence of ice on a pavement is not reliable enough, primarilybecause the temperature differences between pavement surfaceand ambient air vary so greatly Factors such as runway surfacecolor and composition, wind patterns, surface water quantity, icecontrol chemical residue, atmospheric moisture content, traffic,amount of sunlight as well as air temperature all influence iceformation Since ice prevention is more desirable in terms of safety,time savings and cost than ice removal, primary emphasis shouldbe placed on predicting ice before it actually occurs Runway

465


sensors thus are a primary tool in developing an effective iceprevention program S L

N83-25730# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of Systems and LogisticsA PLACEMENT MODEL FOR FLIGHT SIMULATORS M.S.ThesisE P GEBHARD and J P ONEILL Sep 1982 139 p refs(AD-A123782, AFIT-LSSR-23-82) Avail NTIS HC A07/MF A01CSCL 14B

The use of flight simulators has been increasing due to therising costs of operating and maintaining aircraft At the sametime, a drive towards increased simulator fidelity has caused arapid increase in simulator acquisition and support costs The risingcosts of simulator acquisition and support, coupled with the factthat aircrews assigned to any one of the majority of USAF aircrafttypes are stationed at numerous geographic locations, providethe impetus to develop an improved methodology for comparingthe costs of simulator basing strategies The methodology includesa comprehensive analysis of the relevant and significant costs ofsimulator ownership Using these costs as inputs, a computerprogram was developed which incorporates learning curve andpresent value theory into a facility location algorithm The programdetermines the number and location of the simulators to satisfyaircrew training at minimum cost A demonstration of modelcapabilities and a sensitivity analysis based on the acquisition ofthe B-52G Weapon System Trainer are included Author (GRA)

N83-25731# General Accounting Office, Washington, D CFederal Personnel and Compensation DivGREATER BENEFITS TO BE GAINED FROM DOD FLIGHTSIMULATORS14 Nov 1983 19 p(AD-A123713, GAO/FPCD-83-4) Avail NTIS HC A02/MF A01CSCL 05!

Our objectives were to determine whether the services aresufficiently analyzing their training needs and identifying those tasksthat can best be taught on flight simulators, and whether simulatorsare training pilots to do the tasks intended We selected sevenflight simulators that were among the services' highest 20 percentin terms of total dollars invested, were used to train personnel forcritical jobs (tasks that contribute substantially to readiness), andhad been fully operational for at least 2 years The locations wevisited were in geographical areas within large concentrations ofsimulators At each location, we examined course syllabi todetermine how the simulators were to be used We also determinedhow the simulators were being used, benefits derived, and problemswith the simulators GRA

N83-25732# Kaman Avidyne, Burlington, Mass StructuralMechanics SectNOVA-2S CORRELATION WITH KC-135A FUSELAGE SHOCKTUBE TEST RESULTS Final ReportL J MENTE and W N LEE Kirtland AFB, N Mex AFWLNov 1982 138 p refs(Contract F29601-81-C-0031, AF PROJ 8809)(AD-A124013, AFWL-TR-82-101, KA-TR-202) Avail NTIS HCA07/MF A01 CSCL 20D

Correlation of the experimental results from KC-135A fuselagetests in the Sandia shock tube with analytical results generatedthrough the NOVA-2LTS structural response code were performedin this effort It was found that skin buckling between stringerswas a very important factor in the overall response of the framesNOVA-2LTS had to be modified to handle skin buckling in anapproximate manner without generating a prohibitive large solutionmodel Comparisons are made between the experimental resultsand NOVA-2LTS analytical strain results for the unpressunzed andpressurized KC-135A fuselage Overall the strain response resultsfor the central frame correlated well considering the uncertaintiesinvolved in defining structurally an actual large stiffened aircraftsection GRA

N83-25733# Canyon Research Group, Inc, Westlake Village,CalifSIMULATOR DESIGN FEATURES FOR CARRIER LANDING.PART 2. IN-SIMULATOR TRANSFER OF TRAINING InterimTechnical Report, 1 Sep. 1981 • 31 Aug. 1982D P WESTRA Orlando, Fla Naval Training Equipment CenterDec 1982 82 p refs(Contract N61339-81-C-0105)(AD-A124024, NAVTRAEQUIPC-81-0105-1, CRG-TR-82-011)Avail NTIS HC A05/MF A01 CSCL 05!

The Visual Technology Research Simulator (VTRS) at the NavalTraining Equipment Center was used to study the effects of sixfactors on carrier-landing training An in-simulator transfer paradigmwas chosen in which students were trained under various conditionsand then tested under a standard condition that representedmaximum realism The experimental design permitted a relativelylarge number of variables to be studied, using a relatively smallnumber of student subjects Results showed some temporarytransfer advantages for the wide field of view and high scenedetail conditions Training on straight-in approaches resulted intransfer performance that was better than that produced by trainingon circling approaches There was no motion or FLOLS rate cuingeffects on the transfer task Display and simulator transfer effectsdid not differ between the two pilot groups despite large differencesin mean group performances As a result of these findings, it wassuggested that a simulator-to-field transfer study be conductedwith field of view, scene detail and approach type as factorsSuch a study, using pilots from the target population ofundergraduate Naval aviators, would provide the necessaryinformation to make final simulator design decisions for thecarrier-landing task GRA

N83-25735# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringGENERATING AN OUT-THE-WINDOW COCKPIT IMAGE WITHTHE IAPX 432 M.S. ThesisR A COOPER Dec 1982 136 p refs(AD-A124852, AFIT/GCS/EE/82D-12) Avail NTIS HC A07/MFA01 CSCL 09B

The purpose of this thesis investigation is to determine if asmall computer can generate graphic images in a real timeenvironment The specific computer to be used is the Intel lAPX432 Micromainframe The graphic images are to be used as partof an aircraft simulator in a communication performance evaluationtest This thesis investigation contains three areas of study Thefirst investigation is to study the object-oriented architecture ofthe Intel lAPX 432 The second investigation is to examine therequirements of the simulator and produce design andimplementation details The third investigation is aimed at studyingthe F111 DIG ground terrain data base and producing a new database that the small simulator could use GRA

N83-26792# Arizona Umv, Tucson Dept of Aerospace andMechanical EngineeringA NOTE ON ADAPTIVE WIND TUNNELS WITH IMPERFECTCONTROL Final ReportW R SEARS In AFWAL A Collection of Papers in the AerospaceSci p 191-207 Jun 1982 refs(Contract AF-AFOSR-2954E-76)Avail NTIS HC A99/MF A01 CSCL 14B

An earlier study of the convergence of the adaptive wall windtunnel scheme for a sinusoidal model in a two dimensional tunnelis extended to the case where ideal matching at the interfacecannot be achieved It is assumed that, in place of the desiredsinusoidal correction, a correction including an extraneous harmonicalways occurs Two different assumptions are made regarding thefitting of this distorted sinusoid to the observed error signal Theiteration converges for the same range of relaxation constants asfor the ideal case, but that unconfined flow is not achieved Forreasonable numerical values, the iteration nevertheless appearsto make substantial improvement in a flow involving boundaryinterference Author

466

11 CHEMISTRY AND MATERIALS

N83-26849*# Sinacon (John B) Associates, Hollister, CalifRESEARCH AND ANALYSIS OF HEAD-DIRECTEDAREA-OF-INTEREST VISUAL SYSTEM CONCEPTSJ B SINACORI Jun 1983 81 p refs(Contract NAS2-10934)(NASA-CR-166480, NAS 1 26 166480) Avail NTIS HC A05/MFA01 CSCL 14B

An analysis and survey with conjecture supporting a preliminarydata base design is presented The data base is intended for usein a Computer Image Generator visual subsystem for a rotorcraftflight simulator that is used for rotorcraft systems development,not training The approach taken was to attempt to identify thevisual perception strategies used during terrain flight, surveyenvironmental and image generation factors, and meld these intoa preliminary data base design This design is directed at DataBase developers, and hopefully will stimulate and aid their effortsto evolve such a Base that will support simulation of terrain flightoperations Author

10

ASTRONAUTICS

Includes astronautics (general), astrodynamics, ground supportsystems and facilities (space), launch vehicles and space vehicles,space transportation, spacecraft communications, command andtracking, spacecraft design, testing and performance, spacecraftinstrumentation, and spacecraft propulsion and power

after ignition deployment of the EEC and a 30 seconds full scalemotor action test in high altitude simulation Author

A83-36408*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaSPACE-STATION CREW-SAFETY REQUIREMENTSR D WITCOFSKI (NASA, Langley Research Center, Hampton,VA) Conference and Workshops on Mission Assurance, LosAngeles, CA, June 7-9, 1983, Paper 10 p refs

Baseline rescue and survival concepts for future space stationcrews are described Preliminary studies are being carried out toidentify potential threats to crew safety and means to counteractthe dangers Significant factors being considered include the typeof threat, the warning time, the number of crewmembers, strategiesfor protection of the crew (including life-support measuresredundancy), and the dependence of space station crews on groundpersonnel Attention is being given to the impact of safety deviceson the space station geometry and cost, as well as the equipmentnecessary to maintain the crew in a psychological status positiveenough to cope with emergencies Typical threats would be fire,crewmember illness or injury, and abandonment of the station AShuttle launch could take up to 12 days, while equipping thespace station with an emergency return capsule would permit returnon the same day as the capsule was occupied M S K

A83-34849A SMALL PARAMETER METHOD IN PROBLEMS OFMANEUVERING SPACE VEHICLES WITH AERODYNAMICEFFICIENCYV P PLOKHIKH (Tsentral'nyi Aerogidrodinamicheskn Institut,Moscow, USSR) and V V SONIN (Akademua Nauk SSSR, SovetInterkosmos, Moscow, USSR) (International AstronauticalFederation, International Astronautical Congress, 32nd, Rome, Italy,Sept 7-12, 1981) Acta Astronautica (ISSN 0094-5765), vol 10,Jan 1983, p 1-8 refs

An analysis is performed of optimal bank angle and incidencecontrol in the class of piecewise-constant functions for the problemof vehicle aerodynamic maneuvering along a low altitudenear-circular orbit The small parameter method is used to obtainan explicit general solution for adjoint equations system and toderive the vehicle trajectory characteristics The motion is shownto be equivalent to gravitational skipping, irrespective of the valueof vehicle lift-to-drag ratio, similar to Keplenan motion but withcontinuous descent Suggestions for investigating an aerodynamicmaneuver at several turns along a lowering orbit are outlined

Author

A83-36399#DESIGN AND DEVELOPMENT OF A NOZZLE EXTENDIBLE EXITCONEP GENTIL (SocieteEuropeenne de Propulsion,Samt-Medard-en-Jalles, Gironde, France) AIAA, SAE, and ASME,Joint Propulsion Conference, 19th, Seattle, WA, June 27-29, 19837p(AIAA PAPER 83-1410)

Among the various Extendible Exit Cone (EEC) concepts, thefolded petals EEC offers a tight packaging volume associatedwith good area ratio capability The design and development ofsuch a concept is described A first step demonstrated its feasibilitybut the need for some improvements also A second programwas conducted in which development tasks included calculationsof flow pressures, aerodynamic loads and mechanical behavior,subscale mock-up hot firings with high altitude simulation,acceptance bench tests of carbon-carbon components and of thehydraulic deployment device The program was concluded with an

11

CHEMISTRY AND MATERIALS

Includes chemistry and materials (general), composite materials,inorganic and physical chemistry, metallic materials, nonmetallicmaterials, and propellants and fuels

A83-33951HIGHLY STRESSED MATERIALS, WITH AVIATIONCONSIDERED AS AN EXAMPLE [WERKSTOFFE HOHERBEANSPRUCHUNG AM BEISPIEL DER LUFTFAHRT]W BUNK, ED (Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt, Institut fuer Werkstoff-Forschung, Cologne,Aachen, Rhemisch-Westfaehsche Technische Hochschule, Aachen,West Germany) and J HANSEN (Deutsche Forschungs- undVersuchsanstalt fuer Luft- und Raumfahrt, Institut fuerWerkstoff-Forschung, Cologne, West Germany) Oberursel, WestGermany, Deutsche Gesellschaft fuer Metallkunde, 1982, 220 pIn German and English

Materials in the mirror of aviation criteria are considered alongwith structural members made of high-strength cast aluminum andtheir properties, a high-strength aluminum high-quality casting alloyin aeronautics and astronautics, the development and qualificationof welding technology for AZ 5 G (AlZn 4 5 Mg 1) of the Ananeprimary structure, and the development of technical cracks onAI-2024-T3 in the case of one-stage and non-one-stage vibratorystresses Attention is given to a comparison of microstructure andmechanical properties of AI-Li-X alloys made by conventional andby powder-metallurgy procedures, technologies for the productionof titanium and titanium alloys, aspects of metallography andmanufacturing technology regarding the superplastic forming ofTiAI6V4, and powder metallurgy and hot isostatic pressing of thetitanium alloy TiAI6V4 Other subjects investigated are related tooxide dispersion hardened mechanically alloyed materials for hightemperature, and the influence of defects on the operationalstrength of disks and wheels in engines G R

467


A83-33953MATERIAL, STRUCTURAL COMPONENT, SERVICE LIFE[WERKSTOFF - BAUTEIL - LEBENSDAUER]D ENDEMANN (Dormer GmbH, Munich, West Germany), PESSLINGER (Motoren- und Turbinen-Umon Muenchen GmbH,Munich, West Germany), and K SCHRECK (KHD LuftfahrttechnikGmbH, Oberursel, West Germany) IN Highly stressed materials,with aviation considered as an example Oberursel, West Germany,Deutsche Gesellschaft fuer Metallkunde, 1982, p 33-52 InGerman

The present investigation is concerned with problems relatedto a guarantee with respect to a minimum service life for a structuralcomponent The solution of these problems involves basically thedevelopment of an approach by which the failure probability forstructural components can be calculated on a quantitative basisThe ideal conditions for conducting the required calculation can,however, currently not yet be satisfied It is, therefore, necessaryto use generous safety factors Attention is given to structuralcomponents and their defects, approaches for eliminating defects,questions concerning the qualification of material and component,methods for ensuring reproducibihty of the properties of thestructural components of an aircraft, and future aspects related tothe subject of failure probability G R

A83-33954STRUCTURAL MEMBERS MADE OF HIGH-STRENGTH CASTALUMINUM AND THEIR PROPERTIES [BAUTEILE AUSHOCHFESTEM ALUMINIUMGUSS UND DERENEIGENSCHAFTEN]J WEILKE and H FROMMEYER (Veremigte Flugtechnische WerkeGmbH, Bremen, West Germany) IN Highly stressed materials,with aviation considered as an example Oberursel, West Germany,Deutsche Gesellschaft fuer Metallkunde, 1982, p 53-59 InGerman

Structural members made of aluminum casting alloys have beenlittle used in the aviation industry The reasons for this situationare related to the inferior strength of such members when comparedwith components made of wrought-aluminum alloys However,aspects of economics make it now urgently necessary to reducemanufacturing costs by employing structural components made ofcast metal In connection with the absence of extensive machiningrequirements, the manufacturing costs of cast components aregenerally significantly lower than the costs for other partsRequirements regarding a demonstration of economicalachievements and technical reliability are considered It willprobably be possible to satisfy in 1995, for certain componenttypes, up to 40 percent of the requirements with cast parts Theadvantages of modern casting technology compared toconventional manufacturing procedures are illustrated with the aidof a number of examples involving components of the MRCATornado aircraft G R

A83-33955HIGH-STRENGTH ALUMINUM HIGH-QUALITY CASTING ALLOYIN AERONAUTICS AND ASTRONAUTICS [HOCHFESTEALUMINIUM-FEINGUSS-LEGIERUNG IN DER LUFT- UNDRAUMFAHRT]G WEDEKING and CH LIESNER (Titan-Alummium-FeingussGmbH, Bestwig, West Germany) IN Highly stressed materials,with aviation considered as an example Oberursel, West Germany,Deutsche Gesellschaft fuer Metallkunde, 1982, p 61-64 InGerman

The method of investment ('lost wax') casting makes it possibleto produce accurate castings characterized by a high surfacequality Since the obtained cast components are nearly ready forinstallation, an employment of this method leads to savings withrespect to material and to the elimination of many processingstages By combining high-quality casting techniques based oninvestment casting with an employment of suitable alloys ofaluminum, magnesium, titanium, and zirconium, it is feasible tosatisfy the rising demands of modern technology and to reducemanufacturing costs A preferred aluminum alloy with particularlyexcellent casting characteristics is G-AISi7Mg Other alloys

considered include G-AISi7Mg06 and G-AICu4Ag1 It is pointedout that high-strength aluminum alloys can be employed in theaerospace industry for highly stressed structural components

GR

A83-34500THE EFFECT OF PRODUCTS BASED ON HIGHER FATTY ACIDSON THE PERFORMANCE CHARACTERISTICS OF JET FUELS[VLIIANIE PRODUKTOV NA OSNOVE VYSSHIKH ZHIRNYKHKISLOT NA EXPLUATATSIONNYE SVOISTVA REAKTIVNYKHTOPLIV]O P LYKOV, T P VISHNIAKOVA, V V SASHEVSKII, and I EORAKOVA (Moskovskn Institut Neftekhimicheskoi i GazovoiPromyshlennosti, Moscow, USSR) Khimiia i Tekhnologna Topliv iMasel (ISSN 0023-1169), no 5, 1983, p 34-36 In Russian

Higher fatty acids and their oligomers are added to jet fuelsrefined through various hydrogenation processes to improve theirperformance characteristics On the other hand, higher fatty acidsmay have a detrimental effect on the acidity and thermal stabilityof jet fuels Here, a study is made of the properties of the jetfuels T-8, T-8V, and T-7 containing 0 002-0 01 percent by massof additives based on higher fatty acids These include the C17-C20fraction of synthetic fatty acids, isocarbon acids extracted fromthe C17-C20 fraction by acetone, the bottoms of synthetic fattyacid production, and the acids extracted from the bottoms bycold methanol It is found that the additives investigated significantlyimprove the anti-wear characteristics of the jet fuels and do nothave any deleterious effects on the service-related properties ofthe fuels when their concentration does not exceed 0 003 percentby mass V L

A83-35247HIGH TEMPERATURE EROSION STUDY OF INCO 600 METALW TABAKOFF and B V R VITTAL (Cincinnati, University,Cincinnati, OH) Wear (ISSN 0043-1648), vol 86, April 1, 1983,p 89-99 refs(Contract DAAG29-82-K-0029)

The erosive action of high speed particles can cause seriousproblems in connection with a number of applications Applicationsaffected are related to such diverse areas as aircraft gas turbines,rocket nozzles, and coal-fired boiler systems The cost ofmaintaining gas turbines in dusty environments is great Theemployment of air filtration for an alleviation of the problem hasthe disadvantage that both payload and engine performance arereduced The incorporation of erosion as an engine designparameter is considered, taking into account the possibleproduction of an erosion-tolerant engine by the consideredapproach In many turbomachmery applications, erosion takes placeat elevated temperatures near the strength limiting temperature ofthe materials used An erosion test facility was design to provideerosion and rebound data in range of operating temperaturesexperienced in compressors and turbines The test facility wasused to obtain basic erosion data for the INCO 600 material

GR

A83-35811#FURTHER STUDIES ON THE PREDICTION OF SPRAYEVAPORATION RATESJ S CHIN (Beijing Institute of Aeronautics and Astronautics, Beijing,People's Republic of China), A H LEFEBVRE (Purdue University,West Lafayette, IN), and W G FREEMAN IN InternationalSymposium on Air Breathing Engines, 6th, Pans, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 73-78 refs

Predictions based on the Chin, Durrett and Lefebvre (1983)equation for estimating the time required to evaporate any givenfraction of the mass of a liquid fuel spray in stagnant air arecompared with results obtained using a more accurate, but moretedious and time-consuming, iteration procedure Attention is givento aviation gasoline, aviation kerosene, and the light diesel oil DF2, over air pressure and air temperature ranges of 100-2000 kpaand 500-2000 K, respectively The influence of fuel spraycharacteristics is examined by including mean drop size values of

468


30-120 microns in the calculations, while the Rosm-Rammler dropsize distribution parameter is varied from 2 5 to 3 5 The comparisonindicates that the equation proposed yields a simple and effectivemeans for deriving the evaporation times of fuel sprays in stagnantair OC

A83-35813#THE EFFECTS OF FUEL PROPERTIES UPON POLLUTANTSPRESENT IN GAS TURBINE AERO-ENGINESJ ODGERS and D KRETSCHMER (UnwersrteLaval, Quebec,Canada) IN International Symposium on Air Breathing Engines,6th, Pans, France, June 6-10, 1983, Symposium Papers NewYork, American Institute of Aeronautics and Astronautics, 1983, p93-104 Research supported by the Natural Sciences andEngineering Research Council of Canada refs

This paper discusses the probable impact of the alternativefuels upon the pollutants present in the exhaust of aircraft gasturbine The major problem is identified as carbon (soot)Hydrocarbons, carbon monoxide and oxides of nitrogen are alsoconsidered Possible solutions are suggested to minimize thevarious difficulties Other phenomena (atomization, ignition and heattransfer) associated with alternative fuels are lightly touchedupon Author

A83-35821*A STUDY OF LEAN EXTINCTION LIMIT FOR PILOT FLAMEHOLDERX N ZHANG and L Y JIANG (Nanjing Aeronautical Institute,Nanjing, People's Republic of China) IN International Symposiumon Air Breathing Engines, 6th, Pans, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 154-161 refs

An experimental and theoretical study has been carried out todetermine the lean extinction limit of pilot flame holder withhomogeneous mixture Equations of entramments in therecirculation of flame holder have been derived Thesemi-experimental equation has been set up for predicting thelean blow-out equivalent ratio of approach mixture and that of thecorresponding pilot mixture at variable inlet parameters (inlettemperature, pressure, velocity and pilot flow rate) The influenceof blockage of pilot stabilizer is examined Author

A83-35822#EXPERIMENTAL RESEARCH OF THE MECHANISM OF FLAMESTABILIZATION IN TWO PHASE MIXTUREJ -H WANG (Nanjing Aeronautical Institute, Nanjing, People'sRepublic of China) and Y -Z CHANG IN International Symposiumon Air Breathing Engines, 6th, Paris, France, June 6-10, 1983,Symposium Papers New York, American Institute of Aeronauticsand Astronautics, 1983, p 162-171 refs

Pregutter vaporization efficiencies for a turbofan engineafterburner are simulated by the present two-phase mixture testapparatus, together with the inlet temperature and velocity, withinlean flame stability limits The relationship between lean flamestability limits for the cases of homogeneous fuel-air and thetwo-phase mixture have been obtained, allowing semiempmcalformulas for the lean stability limits of a v-gutter flameholder withthree blockage ratios (in a two-phase mixture) to be obtainedFuel film temperature, length and vaporization efficiency are alsoexperimentally investigated O C

A83-36066FLUOROELASTOMERSMaterials and Design (ISSN 0261-3069), vol 4, Feb-Mar 1983,p 657-662 refs

Fluoroelastomers became first available in 1955 The firstcommercial fluoroelastomer was a copolymer of vmyhdene (VF)and chlorotnfluoroethylene (CTFE) These materials are stillavailable today and offer high resistance to chemicals (especiallyacids) and moisture They find applications in pumps, seals, andmeters FKMs still account for the vast maionty of applications offluoroelastomers In addition to FKM elastomers, fluorosiliconeelastomers have been employed for many years These elastomers

have markedly enhanced resistance to fuels and petroleumproducts compared to sihcone They may be flexible to -55 C andbrittle at -66 C, but their long-term heat, stress-relaxation, andchemical resistance is not equal to that of FKM Fluorosiliconeelastomers tend to be used in specialist applications where acombination of heat and fluid resistance and flexibility at subzerotemperature is required Examples are seals and diaphragms inaircraft fuel and hydraulic systems G R

A83-36166* Cincinnati Unw , OhioTHE EFFECT OF MICROSTRUCTURE ON THE FATIGUEBEHAVIOR OF Nl BASE SUPERALLOYSS D ANTOLOVICH (Cincinnati, University, Cincinnati, OH) and NJAYARAMAN IN Fatigue Environment and temperature effects

New York, Plenum Press, 1983, p 119-144 refs(Contract AF-AFOSR-80-0065, NSG-3263)

Nickel-base superalloys are used in jet engine componentssuch as disks, turbine blades, and vanes Improvements in thefatigue behavior will allow the life to be extended or the payloadsto be increased The first part of the present investigation dealsprimarily with the effects of microstructural variations on the fatiguecrack propagation (FCP) behavior of nickel-base alloys, while thesecond part is concerned with low-cycle fatigue (LCF) behavior ofNi base systems Waspaloy at low temperature is considered, takinginto account material heat treatment and test procedures, acomposite plot of Waspaloy FCP data, Pans law fatigue crackpropagation constants, monotonic tensile data, and overload FCPtest results for Waspaloy It is found that the FCP and overloadbehavior of nickel-base alloys may be markedly improved by heattreating Attention is given to effects of cyclic deformation onmicrostructure and substructure, environmental damage, and anenvironmental/deformation model of high temperature LCF G R

A83-36240#FEASIBILITY OF A FULL-SCALE DEGRADER FORANTIMISTING KEROSENER J MANNHEIMER (Southwest Research Institute, San Antonio,TX) AIAA, SAE, and ASME, Joint Propulsion Conference, 19th,Seattle, WA, June 27-29, 1983 8 p Sponsorship U S Departmentof Transportation refs(Contract DOT-FA79WA-4310)(AIAA PAPER 83-1137)

An improved degrader for eliminating fuel filtering andatomization problems with aviation kerosene treated with FM-9polymer to avoid droplet formation in the event of a crash aredescribed The device was based on a prototype model that couldonly process 6 I of fuel (antimistmg kerosene - AMK) The mamfeatures of the degrader comprised an axial piston pump, a needlevalve, and a pressure gage and transducer Maximum flow ratesof 1500 kg/hr were examined, the same as with a JT8D enginein cruise conditions The fuel was heated and cooled to examinedifferent ambient temperature conditions The needle valve featuresa variable area orifice to maintain a constant pressure drop overa wide range of flow rates Measurements were taken of theupstream flow pressure and the ignition of the fuel and it wastound that AMK could be degraded to Jet A performance standardsover any flight conditions, although degradation was more difficultin low-temperature conditions M S K

A83-36241#METHANOL COMBUSTION IN A CF6L-80A ENGINECOMBUSTORW J DODDS, E E EKSTEDT, and D W BAHR (General ElectricCo, Aircraft Engine Business Group, Cincinnati, OH) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 8 p(AIAA PAPER 83-1138)

A series of high pressure tests of a 60 deg sector of a GeneralElectric CF6-80 engine combustor was conducted to evaluateoperation on methanol fuel The use of methanol fuel wassuccessfully demonstrated and, relative to operation with Jet A,provided significant reductions in combustor liner temperatures,flame radiation, and NOx emissions Combustion efficiency and

469


exit temperature profiles were similar with both methanol and JetA Because of the low heating value of methanol, fuel flow levelshad to be more than doubled at all power levels, relative to thoseneeded with Jet A, to satisfy engine turbine inlet temperaturerequirements Author

A83-36243#THERMAL STABILITY OF ALTERNATIVE AIRCRAFT FUELSJ TEVELDE, L J SPADACCINI, E J SZETELA (UnitedTechnologies Research Center, East Hartford, CT), and M RGLICKSTEIN (United Technologies Corp , Pratt and Whitney Group,West Palm Beach, FL) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 8 p refs(Contract N00140-80-C-0097)(AIAA PAPER 83-1143)

A heated-tube apparatus was used to evaluate the thermalstability characteristics of four liquid hydrocarbon fuels and todetermine the effect fuel deposits have on the heat transfercharacteristics of aircraft gas turbine fuel systems The fuels testedwere a low-aromatic JP-5, a blend of 80 percent JP-5 and 20percent hydrocracked gas oil, a blend of 50 percent JP-5 and 50percent No 2 heating oil, and a shale derived JP-5 Depositformation rates ranging from 10 to 3000 microgram/sq cm hrwere obtained at tube wall temperatures ranging from 480 to 800K, with peak formation rates occurring at initial surface temperaturesof 644 to 672 K Results indicate that deposit formation rate (1)correlates very well with initial surface temperature and (2) isrelatively insensitive to fuel pressure in the range from 27 2 to544 atm, and test duration in the range from 1 to 14 hr Thedeposit thermal resistance, as calculated from heat transfermeasurements, correlates well with measured deposit quantity andthickness Author

N83-25790*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioEVALUATION OF LOW-COST ALUMINUM COMPOSITES FORAIRCRAFT ENGINE STRUCTURAL APPLICATIONSD L MCDANIELS and R A SIGNORELLI 1983 31 p refsPresented at the 112th Ann Meeting of the Met Soc of the AmInst of Mining, Met and Petroleum Engineers, Atlanta, 6-10 Mar1983(NASA-TM-83357, E-1618, NAS 1 1583357) Avail NTIS HCA03/MF A01 CSCL11D

Panels of discontinuous SiC composites, with several aluminummatrices, were fabricated and evaluated Modulus, yield strengthand tensile strength results indicated that the properties ofcomposites containing SiC whisker, nodule or particulatereinforcements were similar The modulus of the composites wascontrolled by the volume percentage of the SiC reinforcementcontent, while the strength and ductility were controlled by boththe reinforcement content and the matrix alloy The feasibility offabricating structural shapes by both wire performs and directcasting was demonstrated for AI2O3/AI composites The feasibilityof fabricating high performance composites into structural shapesby low pressure hot molding was demonstrated for B4C-coatedB/AI composites Author

N83-25793# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringA PARAMETRIC STUDY OF SURFACE IMPERFECTIONS ANDSMALL CUTOUTS IN A COMPOSITE PANEL M.S ThesisT C JANISSE Dec 1982 168 p refs(AD-A124739, AFIT/GAE/AA/82D-15) Avail NTIS HC A08/MFA01 CSCL 12A

A finite element computer code, STAGS C-1, was used tostudy the effects surface imperfections and cutouts have on theload bearing capability and the displacement patterns of agraphite-epoxy panel A nonlinear collapse analysis was conductedon two different ply layups each with five different surfaceimperfection patterns In addition three different ply orientationswere studied each having two different size cutouts (a two inchby two inch square and a four inch by four inch square) Thenonlinear branch of STAGS C-1 uses a energy technique using

the nonlinear stiffness matrix that was generated by using theSanders' strain displacement equations STAGS did a very goodjob in calculating the collapse load and displacement of a panelwith surface imperfections when compared with experimentallytested panel The collapse characteristics of composite panelsare dependent on the ply layup and size of the cutout Smallcutouts had a displacement pattern that was not expected and isdifferent than the larger cutouts Changing the vertical boundaryconditions on the panel with the small cutout had a negligibleeffect GRA

N83-25795# Atlantic Research Corp , Alexandria, VaCOMPOSITE MATERIAL AIRCRAFT ELECTROMAGNETICPROPERTIES AND DESIGN GUIDELINESJ A BIRKEN, W G DUFF, D R PFLUG, and R AWALLENBERG Oct 1981 369 p refs(Contract N00019-79-C-0634)(AD-A124016) Avail NTIS HC A16/MF A01 CSCL 01C

This document collects and primarily summarizes aircraftadvanced composite material electromagnetic properties, andsecondarily, summarizes composite material mechanical, thermal,environmental, fabrication properties noting their ramifications onelectromagnetic performance It, then, overviews theelectromagnetic sub-disciplines of threats, external to internalaircraft coupling, component and subsystems susceptibilityprotective methods as well as test and evaluation of small sampleto total aircraft composite material electromagnetic performanceThe sub-disciplines constitute a partioned set of independentvariables which allow the reader to locate his area of interest inone section of the book The sub-discipline are then combined toperform total aircraft electromagnetic system performance notingthe protective methods, advantages and penalties

Author (GRA)

N83-25829# Naval Postgraduate School, Monterey, Calif Deptof AeronauticsAUTOMATIC CONTROL AND DATA ACQUISITION SYSTEMFOR COMBUSTION LABORATORY APPLICATIONS M.S ThesisB J HANSEN Oct 1982 120 p refs(AD-A125195) Avail NTIS HC A06/MF A01 CSCL21B

A modern computer based automatic data acquisition/controlsystem was installed at the Department of Aeronautics' CombustionLaboratory This system utilizes an HP-85 desktop computer assystem controller for the HP-3054A data acquisition system Largequantities of high quality data can be acquired at high data ratesand stored for future use or processed real time in closed loopfeedback control circuits for precise process control and displayOther electromechanical equipment such as Visicorders provideanalog real time data and run in parallel with digital equipmentbut can be remotely controlled for precise timing of experimentsInteractive programs on the HP-85 computer allow the experimenterto do preliminary calculations, initial experiment set-up, and toperform accurate process control of system functions On linedata reduction and display of results is performed by the systemCRT display, the 7225B Plotter, or the system printer Four basicexperiments/experimental apparatuses are currently automatedusing the automatic data acquisition system, a light scatteringexperiment, a vitiated air heater, a solid fuel ramjet, and a turbojetcombustor test rig The first three applications are discussed insubsequent sections along with the measurement techniques usedto implement the process Author (GRA)

N83-25854*# National Aeronautics and Space AdministrationMarshall Space Flight Center, Huntsville, AlaPRELIMINARY SCIENCE REPORT ON THE DIRECTIONALSOLIDIFICATION OF HYPEREUTECTIC CAST IRON DURINGKC-135 LOW-G MANEUVERSP A CURRERI, D M STEFANESCU, and J C HENDRIX Apr1983 23 p refs(NASA-TM-82528, NAS 1 1582528) Avail NTIS HC A02/MFA01 CSCL11F

An ADSS-P directional solidification furnace was reconfiguredfor operation on the KC-135 low-g aircraft The system offers

470


many advantages over quench ingot methods for study of theeffects of sedimentation and convection on alloy formation Thedirectional sodification furnace system was first flown during theSeptember 1982 series of flights The microstructure of thehypereutectic cast iron sample solidified on one of these flightssuggests a low-g effect on graphite morphology Furtherexperiments are needed to ascertain that this effect is due tolow-gravity and to deduce which of the possible mechanisms isresponsible for it Author

N83-25904# Southwest Research Inst, San Antonio, Tex Fuelsand Lubricants Research LabEMERGENCY FUELS TECHNOLOGY Interim Report, May 1981- Jun. 1982J N BOWDEN and L I STAVINOHA Jun 1982 84 p refs(Contract DAAK70-80-C-0001, DAAK70-82-C-0001, DA PROJ1L7-72733-AH-20)(AD-A125275, AFLRL-155, SWRI-6800-129) Avail NTIS HCA05/MF A01 CSCL21D

Different types of engines in the military system require specificfuels for normal operation Spark-ignition engines require gasoline,compression-ignition engines and ground gas turbine enginesrequire diesel fuel The requirements of each engine type arelisted in Army Regulation 703-1 as primary, alternate andemergency fuels The work reported here identifies othercombustible liquids that, in extreme emergency scenarios, couldbe used as field emergency fuels (FEF), either as extenders ofthe primary fuel supply, or as acquired Correlations are presentedthat permit estimating the fuel blend properties considered to becrucial for operation of engines at a minimal performance level

Author (GRA)

N83-26929# Ohio State Univ , ColumbusTRANSIENT HEAT FLOW ALONG UNI-DIRECTIONAL FIBERSIN COMPOSITES Final Report, 1 Jul. 1978 - 31 Dec. 1981L S HAN Wright-Patterson AFB, Ohio AFWAL Dec 1982147 p(Contract AF-AFOSR-3640-78, AF PROJ 2307)(AD-A122926, AFWAL-TR-82-3061, REPT-761108/711129)Avail NTIS HC A07/MF A01 CSCL 11D

For uni-directional fibrous composites and laminatedcomposites, a heat balance integral method has been developedfor the analysis of transient heat flow along the fibers or in theplane of laminates The method is based on the construction of,for the two constituent media, temperature profiles which not onlysatisfy the necessary boundary conditions but also fulfill theasymptotic error function properties When inter-region conductionis vanishmgly small or at very early times of the heat transientBy comparing with the results of exact solutions, accuracy of themethod has been established to be dependent on a number offactors especially the inter-face conduction coefficient and thermalcapacity ratio For the case of a constant surface heat flux, arelevant engineering problem, surface temperature rises of thetwo regions may be quite different from each other Temperaturedifferences, however, dimmish quite rapidly toward the interior andare only confined to a depth equal to a few fiber radii or laminatethicknesses Author

N83-26934# ECON, Inc, Princeton, N JSTATUS, TRENDS AND IMPLICATIONS OF CARBON FIBERMATERIAL USE Final Report, 20 Sep. 1979 - 19 Sep. 1981Dec 1982 160 p refs(Contract EPA-68-03-2857)(PB83-147751, EPA-600/2-82-103) Avail NTIS HC A08/MFA01 CSCL11D

The future usage of carbon fiber composite materials in bothconsumer and industrial products, and the resultant economicimpact of the disposal of these products and industrial scrap inboth the municipal and industrial waste streams are estimatedThe technical and economic substitutability of carbon fibercomposite materials for materials now in use is analyzed, and themajor uses of this material forecasted Potential problems relatingto the disposal of products containing carbon fiber materials are

analyzed, and estimates made of the economic impacts of thedisposal of these products for alternative scananos that cover awide range of disposal technologies The economic impact of thedisposal of products and industrial scrap containing carbon fibercomposite materials is found to be insignificant for all of thescananos investigated GRA

N83-27033# Virginia Polytechnic Inst and State Univ , BlacksburgDept of Aerospace and Ocean EngineeringINJECTION, ATOMIZATION, IGNITION AND COMBUSTION OFLIQUID FUELS IN HIGH-SPEED AIR STREAMS Final Report, 1Dec. 1978 - 30 Nov. 1981J A SCHETZ Nov 1982 25 p(Contract AF-AFOSR-3485-78, AF PROJ 2308)(AD-A125237, VPI-AERO-130, AFOSR-83-0025TR) Avail NTISHC A02/MF A01 CSCL 21B

Experimental studies of the penetration, break-up andatomization of transverse liquid and slurry jets were performedAll tests were with an air cross flow at Mach 3 0 with Po = 4atm and To = 300 deg K The processes studied were (1) theeffects of mjectant viscosity and surface tension, (2) theperformance of an impinging jet injector and (3) the effects ofparticle loading for a slurry jet with 3-50 micrometer particles Thediffractively scattered light method was employed at thesehigh-density, supersonic conditions to study droplet sizes Themajor results are, (1) mean droplet size is approximately 10 micronsfor injectors of 0 05 in, (2) it has an inverse relation with jet/freestream dynamic pressure ratio, (3) it has a direct relation withorifice diameter, (4) it decreases downstream, (5) transversevariation has no simple pattern and (6) droplet size increaseswith viscosity GRA

N83-27034# Naval Postgraduate School, Monterey, CalifAN INVESTIGATION OF THE EFFECTIVENESS OF SMOKESUPPRESSANT FUEL ADDITIVES FOR TURBOJETAPPLICATIONS M.S. ThesisJ R BRAMER Oct 1982 72 p refs(AD-A125025) Avail NTIS HC A04/MF A01 CSCL 21E

Seven fuel additives were tested to investigate theireffectiveness at reducing exhaust stack gas opacity in a turbojettest cell Exhaust particle sizes and mass concentrations weredetermined at the engine and stack exhausts using measurementsof light transmittance at three frequencies Particle samples werealso collected at the engine exhaust and measured with a scanningelectron microscope to verify the optical technique Nitrous oxideemissions were measured at the test cell stack exhaust Four ofthe additives tested were found effective at reducing stack exhaustopacity and paniculate mass concentration None of the additiveshad any measurable effect on particle diameters No meaningfulchanges in particle size or mass occurred between the engineand stack exhausts The optical technique for determining particlesize was verified effective using the scanning electron microscopeNo additive had any significant effect on nitrous oxide production

Author (GRA)

N83-27035# California Univ, Riverside Pollution ResearchCenterHIGH ALTITUDE JET FUEL PHOTOCHEMISTRY Final Report,Nov. 1980 • Sep. 1982A M WINER, R ATKINSON, W P L CARTER, W D LONG, SM ASCHMANN, and J N PITTS, JR Tyndall AFB, Fla AirForce Engineering and Services Center Oct 1982 164 p refs(Contract F08635-80-C-0359, AF PROJ 1900)(AD-A125035, AFESC/ESL-TR-82-38) Avail NTIS HC A08/MFA01 CSCL 21D

Military jet aircraft flight procedures make it necessary to jettisonexcess fuel in the event of certain in-flight operational situationsThese fuel expulsions can be sizable, and in the presence ofsunlight and NOx emissions from engine exhaust there exists thepotential for formation of ozone and other manifestations ofphotochemical smog Since these fuel dumping procedures arecarried out at elevated altitudes the atmospheric properties involved

471

12 ENGINEERING

are significantly different from those at ground levelAuthor (GRA)

12

ENGINEERING

Includes engineering (general), communications, electronics andelectrical engineering, fluid mechanics and heat transfer,instrumentation and photography, lasers and masers, mechanicalengineering, quality assurance and reliability, and structuralmechanics

A83-33507EVALUATION OF THE EFFECT OF VOIDS IN COMPOSITE MAINROTOR BLADESD G ORLINO (U S Army Applied Technology Laboratory, FortEustis, VA), R J SHUFORD, and W W HOUGHTON (U S Army,Army Materials and Mechanics Research Center, Watertown, MA)American Helicopter Society, Journal (ISSN 0002-8711), vol 27,Oct 1982, p 49-56

Design and fabrication of the Improved Mam Rotor Blade,designated K-747, as a replacement for the Bell Model AH-1SCobra, evolved through mission requirements necessitating higherarmament payloads, and thus a need to improve rotor liftingcapacity Required increases in performance appeared to beobtainable by directly replacing the mam rotor blades with newblades having increased aerodynamic efficiency Attention wasgiven to a test program directed at assessing void growthcharacteristics and rates for composite structures A descriptionis presented of void growth measurements conducted in connectionwith fatigue testing one K-747 mam rotor blade for 29 millioncycles, taking into account the nondestructive techniques usedduring the test program G R

A83-33650MICROECONOMIC MODELS FOR PROCESS DEVELOPMENTV A TIPNIS, U WATWE (Tipnis Associates, Inc , Cincinnati, OH),S J MANTEL, JR (Cincinnati, University, Cincinnati, OH), and GL RAVIGNANI IN Advanced processing methods for titanium,Proceedings of the Symposium, Louisville, KY, October 13-15, 1981

Warrendale, PA, Metallurgical Society of AIME, 1982, p289-308 refs(Contract F33615-79-C-5119)

The evaluation of return on added investments, and economicsensitivities during process development, have been introducedinto the 'macro', or processing sequence level, and 'micro', orcut/stroke level, in order to identify opportunity windows, andranges of operating variables, within which a novel process canbe made competitive with existing ones The process modelconsists of process inputs, constraints, and outputs for the unitunder investigation, and is ultimately related to phenomenologicalmodels derived from constitutive relationships, interfacephenomena such as friction and wear, and fracture limit instabilityThe microeconomic model is based on the process model at thelevel of the processing unit The overall relationship between theprocess and miroeconomic models is presently investigated forthe case of Ti airframe milling O C

A83-33964THE INFLUENCE OF DEFECTS ON THE OPERATIONALSTRENGTH OF DISKS AND WHEELS IN ENGINES[FEHLEREINFLUSS AUF DIE BETRIEBSFESTIGKEIT VONTRIEBWERKSSCHEIBEN UND -RAEDERN]G KOENIG and J WORTMANN (Motoren- und Turbmen UnionMuenchen GmbH, Munich, West Germany) IN Highly stressedmaterials, with aviation considered as an example Oberursel,West Germany, Deutsche Gesellschaft fuer Metallkunde, 1982, p155-167 In German

It is pointed out that rotating parts belong to those componentsof an aircraft engine which have to satisfy the most exactingsafety requirements Safety hazards are related to the risk of enginefailure, and, in addition, also to the possibly very serious effectswhich can be produced in connection with the rupture of a rotatingcomponent with its enormous kinetic energy The relative frequencyof an occurrence of various types of failure mechanisms isconsidered, taking into account also the relative importance ofthe responsible causes Low-frequency cyclic stresses related tochanges in the rotational speed in connection with changes fromone flight phase to another are found to be particularly criticalAttention is given to the sections of a component for which thepossibility of crack formation is especially great, aspects of crackpropagation, the maximum size of defects which cannot bediscovered with the employed inspection methods, the effect ofdefects on operational conditions, and the results of testsconducted with disks made of various materials G R

A83-33974RESIDUAL LIFE PREDICTION FOR JET ENGINE ROTOR DISKSAT ELEVATED TEMPERATUREH OHNABE, M ZAKO, T KAWASHIMA (Ishikawajima-HanmaHeavy Industries Co , Ltd , Tokyo, Japan), and T MIYOSHI (Tokyo,University, Tokyo, Japan) Metallurgical Society of AIME, AnnualMeeting, 111th, Dallas, TX, Feb 14-18, 1982, Paper 11 p refs

The life prediction method of rotor disks at elevatedtemperatures is presented, assuming crack initiation to occur atthe rim slot of an aircraft jet engine rotor disk and converting thetwo-dimensional stress into a quasi-three-dimensional one Thermaland centrifugal stress at the cracked part of the rim slot is calculatedby the finite element method, and Pans's rule is used for calculationof the crack propagation Assuming Klc and the difference betweenKlc and calculated Kl, that is, Klc - Kl, to be a Gaussian distribution,safety is estimated by the relationship between fracture probabilityand standard deviation In the numerical examples, an ellipticsurface crack being assumed at three different parts of the rimslot of a rotor disk at elevated temperature, the crack propagationafter the 2000th cycle is calculated and then compared with thecase of constant (room) temperature The safety of rotor disks isjudged by the value of Klc - Kl Author

A83-34170LASERS IN AIRCRAFT CONSTRUCTION [LAZERY VSAMOLETOSTROENII]E T VAGNER Moscow, Izdatel'stvo Mashmostroenie, 1982,184 p In Russian refs

Theoretical considerations and practical results concerning theapplication of lasers in aircraft construction and production aregeneralized and systematized Particular attention is given to thetheoretical principles underlying relativistic laser metrology, laserinterferometers, laser aligning systems, the use of laser measuringsystems in assembly processes, and the effect of environmentalconditions on the operation of laser aligning systems, andmeasurement errors B J

A83-34311OPTIMIZATION FOR STRUCTURES OF DISCRETE-SIZEELEMENTSH M HUA (Aero Industry Development Center, Republic ofChina) Computers and Structures (ISSN 0045-7949), vol 17, no3, 1983, p 327-333 refs

An optimization algorithm for finding the minimum weight designof a structure assembled with material of discrete sizes is

472

12 ENGINEERING

presented Examples of the use of this method for aerospacestructure design problems are presented, including the four-barspace truss, the ten-bar truss, and the eighteen-member wingbox The results of these examples show that the structures underdisplacement and stress constraints can be optimized by usingthis search algorithm Although the algorithm is formulated to findthe feasible solution through direct evaluation, it can be extendedeasily to solving the optimization problem with dynamic constraintsThe method is very flexible and it can be applied to selecting anoptimal design among the material available and to determiningthe optimal fiber layer distribution of various orientations in thestructures of composite materials N B

A83-34315NONLINEAR SUPERSONIC FLUTTER OF PANELSCONSIDERING SHEAR DEFORMATION AND ROTARYINERTIAK S RAO and G V RAO (Indian Space Research Organization,Vikram Sarabhai Space Centre, Div , Trivandrum, India) Computersand Structures (ISSN 0045-7949), vol 17, no 3, 1983, p361-364 refs

The finite element method is employed to study the nonlinearsupersonic flutter of panels for end conditions of simply supported,clamped, and partial restraint against rotation The effect of sheardeformation and rotary inertia on the nonlinear flutter boundary isinvestigated for varying thicknesses of the panel Results showthat shear and rotary inertia reduce the critical dynamic pressureparameter, while the large deflection increases the critical dynamicpressure parameter It is concluded that for panels with L/h lessthan or equal to 10, where L is the length of the panel and h isthe thickness of the panel, the shear and rotary inertia effects areconsiderable and should be included N B

A83-34472THE DISTRIBUTION OF THE DISPERSE FRACTION OF APOLYDISPERSE JET INJECTED INTO A GAS FLOW [ORASPREDELENII V GAZOVOM POTOKE DISPERGIROVANNOIFRAKTSII IZ VVODIMOI V NEGO POLIDISPERSNOI STRUI]I L MOSTINSKII, D I LAMDEN, and O G STONIK (AkademnaNauk SSR, Institut Vysokikh Temperatur, Moscow, USSR)Inzhenerno-Fizicheskn Zhurnal (ISSN 0021-0285), vol 44, May1983, p 739-748 In Russian refs

Analytical expressions describing the distribution of apolydisperse jet in a gas flow are obtained, and the cases oflongitudinal and transverse aerosol injection are examined Thespray geometry and the droplet size distribution functions are usedin sufficiently arbitrary form and are suitable for both direct-jetand centrifugal nozzles The solutions employ relationships forthe trajectories of individual droplets that have been obtained byusing an empirical drag coefficient in a two-dimensional equationof motion The resulting expressions for the disperse phasedistribution over the flow cross section are reduced to a formconvenient for engineering applications Illustrative examples aregiven V L

A83-34744ON IMPROVING THE FATIGUE PERFORMANCE OF ADOUBLE-SHEAR LAP JOINTL SCHWARMANN (Veremigte Flugtechnische Werke GmbH,Bremen, West Germany) International Journal of Fatigue (ISSN0142-1123), vol 5, April 1983, p 105-111 Research sponsoredby the Bundesmmisterium der Verteidigung refs

Different methods of improving the fatigue performance of adouble-shear lap joint which is representative for airframe structuresare discussed. Considering all aspects concerning fatigueperformance, fabrication problems and costs, one method isrecommended for practical application in aviation This methodinvolves the installation of cylindrical fasteners with a low degreeof interference-fit into cold-worked holes Author

A83-35040VIBRATIONAL DIAGNOSTICS OF GAS-TURBINE BLADES[VIBRODIAGNOSTIKA RABOCHIKH LOPATOKGAZOTURBINNYKH USTANOVOK]E A IGUMENTSEV (Nauchno-Proizvodstvennoe Ob'edmemeSoiuzturbogaz, Kharkov, Ukrainian SSR) Problemy Prochnosti(ISSN 0556-171X), May 1983, p 40-44 In Russian refs

A stochastic method is proposed for the diagnostics ofresonance stresses in the blading of gas turbines on the basis ofthe torsional vibrations of the rotor The principal probabilitycharacteristics of the blade dynamics essential for the diagnosisare determined The suitability of the proposed relationships forpractical calculations is demonstrated by an example V L

A83-35809#EFFECT OF AIR, LIQUID AND INJECTOR GEOMETRYVARIABLES UPON THE PERFORMANCE OF A PLAIN-JETAIRBLAST ATOMIZERG A HUSSEIN, A K JASUJA, and R S FLETCHER (CranfieldInstitute of Technology, Cranfield, Beds , England) IN InternationalSymposium on Air Breathing Engines, 6th, Pans, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 56-63 refs

Plain air jet air blast atomizer design is undertaken, on thebasis of an examination of the breakup characteristics of a discreteliquid jet that is injected into a high velocity cross-flowing airstream,where the variables considered are airstream velocity, liquid jetvelocity, injection orifice diameter, liquid viscosity, and liquid surfacetension Tests were conducted in normal atmospheric pressureand temperature conditions, using a laser light scattering techniquefor mean drop size determination O C

A83-35810#FURTHER STUDY ON THE PREDICTION OF LIQUID FUELSPRAY CAPTURE BY V-GUTTER DOWNSTREAM OF A PLAINORIFICE INJECTOR UNDER UNIFORM CROSS AIR FLOWM -H CAO and J -S CHIN (Beijing Institute of Aeronautics andAstronautics, Beijing, People's Republic of China) IN InternationalSymposium on Air Breathing Engines, 6th, Pans, France, June6-10, 1983, Symposium Papers New York, American Institute ofAeronautics and Astronautics, 1983, p 64-72 refs

On the basis of the Chin and Cao (1983) flat fan spray andfuel capture models, flame holder liquid fuel spray capture ispredicted in route to a consideration of the effect of differentfactors on fuel spray capture for a wide range of parameters Acomparison is then undertaken between fuel spray capture byvertically and horizontally positioned flame holders, and acorrelation for maximum fuel spray capture is determined Theresults obtained indicate that the vertically positioned flame holderprovides more effective fuel capture, as well as the ability to changefuel capture over a wide range through simple alteration ofjuxtaposition distance O C

A83-35862#EXPERIMENTAL INVESTIGATION ON THE ROLE OFFLEXBARS AND METALLIC END SEALS IN SQUEEZE FILMDAMPERSV A KUMAR (National Aeronautical Laboratory, Bangalore, India),S C KAUSHAL, and K LAKSHMIKANTAN (GTRE, Research Div,Bangalore, India) IN International Symposium on Air BreathingEngines, 6th, Paris, France, June 6-10, 1983, Symposium Papers


A performance evaluation is undertaken for squeeze filmdampers by means of a novel test program which highlights theeffect of several related parameters on damper performanceAttention is given to the effects of flexbars and metallic end sealson the performance of squeeze film dampers Damping coefficientquantitative values were calculated by direct measurement of theforce transmitted to the foundation, damper sleeve displacement,phase angle between force transmitted and damper sleevedisplacement, and excitation frequency, for various oil supplypressures and rotor speeds Flexbars and metallic end seals

473

12 ENGINEERING

generally improve system damping characteristics, and it is notedthat the location of the end seal gap, in relation to the position ofthe squeeze film oil supply inlet ports, plays a significant role inmaking the introduction of the end seal more effective in systemdamping O C

A83-35933INTEGRO-DIFFERENTIAL EQUATIONS OF THE DYNAMICS OFELASTIC SYSTEMS IN NONSTATIONARY FLOWS[INTEGRO-DIFFERENTSIAL'NYE URAVNENIIA DINAMIKIUPRUGIKH SISTEW) V NESTATSIONARNOM POTOKE]V I MOROZOV and A T PONOMAREV (Voenno-VozdushnaiaInzhenernaia Akademna, Moscow, USSR) Prikladnaia mekhanika(ISSN 0032-8243), vol 19, May 1983, p 128-131 In Russianrefs

A mathematical model of nonstationary aeroelasticity has beendeveloped by combining the numerical methods of aerodynamicswith elasticity theory The aerodynamics is described using alinearized approach, in the elastic part of the problem, both linearand nonlinear relationships are employed The two parts arecombined by using the convolution for determining the variablepressure fields The possibilities of the model are illustrated byexamples involving the behavior of a flight vehicle as a wholeand its components in turbulent nonseparated flow Results arepresented in graphical form V L

A83-36039*# National Aeronautics and Space AdministrationLangley Research Center, Hampton, VaEVALUATION OF A SURFACE PANEL METHOD COUPLEDWITH SEVERAL BOUNDARY LAYER ANALYSESS O KJELGAARD (NASA, Langley Research Center, Low-SpeedAerodynamics Div, Analytical Methods Branch, Hampton, VA)American Institute of Aeronautics and Astronautics, AerospaceSciences Meeting, 21st, Reno, NV, Jan 10-13, 1983 9 p refs(AIAA PAPER 83-0011)

Three boundary layer models are interacted with an inviscidpanel method to evaluate their capabilities to predict aerodynamicperformance characteristics These boundary layer models includetwo two-dimensional boundary layer models and onethree-dimensional boundary layer model Previously reporteddiscrepancies between the transpiration and surface displacementinviscid boundary layer simulations are discussed and resolvedResults from each of the models are compared with experimentaldata Author

A83-36085*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifSEVEN-HOLE CONE PROBES FOR HIGH ANGLE FLOWMEASUREMENT THEORY AND CALIBRATIONK N EVERETT, A A GERNER, and D A DURSTON (NASA,Ames Research Center, Moffett Field, CA) AIAA Journal (ISSN0001-1452), vol 21, July 1983, p 992-998 refs

Previously cited in issue 08, p 1219, Accession noA82-22070

A83-36174LIFE PREDICTION FOR TURBINE ENGINE COMPONENTST NICHOLAS and J M LARSEN (USAF, Wright AeronauticalLaboratories, Wright-Patterson AFB, OH) IN Fatigue Environmentand temperature effects New York, Plenum Press, 1983, p353-375 USAF-supported research refs

An alternate approach to life management of turbine enginesis being considered considered by the U S Air Force Whereasmost major structural components are currently limited by lowcycle fatigue and are retired fro service after their design life hasbeen reached, a 'Retirement for Cause' approach would keepcomponents in service until a fatigue crack has been detectedThe approach is based on non-destructive inspection and predictionof fatigue crack growth behavior under engine operating conditionsThis paper discusses the concept of retirement for cause andreviews the problems associated with the prediction of crackgrowth Several aspects of crack growth under engine spectrumloading including creep crack growth and crack retardation are

discussed Recommendations for future research efforts arepresented Author

A83-36221#DESIGN OF A REAL-TIME CGSI SYSTEMD M BALDWIN (U S Navy, Naval Training Equipment Center,Orlando, FL), B F GOLDIEZ (U S Army, Orlando, FL), and C PGRAF (Honeywell Systems and Research Center, Minneapolis,MN) IN Flight Simulation Technologies Conference, NiagaraFalls, NY, June 13-15, 1983, Collection of Technical PapersNew York, American Institute of Aeronautics and Astronautics,1983, p 154-162(AIAA PAPER 83-1101)

A hybrid system, CGSI, is being developed which will mergethe attributes of video disc technology and Computer GeneratedImagery (CGI) Initial non-real time feasibility has beendemonstrated and reported on Detailed design of a limited real-timesystem is being conducted The basic design is modular with aparallel pipeline architecture This real-time design is the topic ofthis paper Author

A83-36237#ECCENTRIC END WEAR IN CYLINDRICAL ROLLER BEARINGSCAN BE PREDICTED AND PREVENTEDW E POOLE and G E CHETTA (United Technologies Corp,Pratt and Whitney Group, West Palm Beach, FL) AIAA, SAE,and ASME, Joint Propulsion Conference, 19th, Seattle, WA, June27-29, 1983 7 p(AIAA PAPER 83-1132)

Cylindrical roller bearings are widely used for rotor support ingas turbine engines because of their high load capacity, suitabilityfor high speed and their capability to allow relative axial movementbetween the engine rotor and case However, problems may arise,as the gas turbine environment becomes more demandingAlthough not new, eccentric end wear occurs more frequentlyand may progress to secondary engine damage more rapidly inmodern high speed turbine engines Several theories weredeveloped as potential causes of eccentric end wear based onearlier work A test program was structured to evaluate each theorywith the goal of duplicating the cage fracture sequence in a bearingrig and, if successful, in an engine It is found that wear can beinitiated by roller dynamic unbalance Other observed causes ofeccentric end wear are local end defects and end runout Highinternal radial clearance contributes to wear progression Wearprogression leading to large end runout depends only ongeometry G R

A83-36239*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioDESIGN ANALYSIS OF A SELF-ACTING SPIRAL-GROOVE RINGSEAL FOR COUNTER-ROTATING SHAFTSEL Dl RUSSO (NASA, Lewis Research Center, Cleveland, OH)AIAA, SAE, and ASME, Joint Propulsion Conference, 19th, Seattle,WA, June 27-29, 1983 8 p(AIAA PAPER 83-1134)

A self-acting spiral groove inter-shaft ring seal of nominal 16 33cm (6 43 in) diameter for sealing fan bleed air between counterrotating shafts in advanced turbofan engines was analyzed Theanalysis focused on the lift force characteristics of the spiralgrooves A NASA Lewis developed computer program for predictingthe performance of gas lubricated face seals was used to optimizethe spiral groove geometry to produce maximum lift force Loadcapacity curves (lift force as function of film thickness) weregenerated for four advanced turbofan engine operating conditionsat relative seal speeds ranging from 17,850 to 29,800 rpm, sealedair pressures from 6 to 42 N/sq cm (9 to 60 Psi) absolute andtemperatures from 95 to 327 C (203 to 620 F) The relative sealsliding speed range was 152 to 255 m/sec (500 to 836 ft/sec)The analysis showed that the spiral grooves are capable ofproducing sufficient lift force such that the ring seal will operatein a noncontactmg mode over the operating range of typicaladvanced turbofan engines Previously announced in STAR asN83-23306 Author

474

12 ENGINEERING

A83-36277*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioEXPERIMENTS IN DILUTION JET MIXINGJ D HOLDEMAN (NASA, Lewis Research Center, Cleveland, OH),R SRINIVASAN, and A BERENFELD (Garrett Turbine Engine Co ,Phoenix, AZ) AIAA, SAE, and ASME, Joint Propulsion Conference,19th, Seattle, WA, June 27-29, 1983 14 p refs(AIAA PAPER 83-1201)

Experimental results are presented on the mixing of a singlerow of jets with an isothermal mainstream in a straight duct, withflow and geometric variations typical of combustion chambers ingas turbine engines included It is found that at a constantmomentum ratio, variations in the density ratio have only asecond-order effect on the profiles A first-order approximation tothe mixing of jets with a variable temperature mainstream can, itis found, be obtained by superimposing thejets-in-an-isothermal-crossflow and mainstream profiles Anotherfinding is that the flow area convergence, especially injection-wallconvergence, significantly improves the mixing For opposed rowsof jets with the orifice cone centerhnes in-line, the optimum ratioof orifice spacing to duct height is determined to be 1/2 of theoptimum value for single injection at the same momentum ratioFor opposed rows of jets with the orifice centerhnes staggered,the optimum ratio of orifice spacing to duct height is found to betwice the optimum value for single side injection at the samemomentum ratio C R

Promising lubricants include MoS2, graphite, WSe2-Galn, andAgHg-PTFE-MoS2 Attempts at simulating dry lubricated bearingbehavior and performance by computer program are outlined

MSK

A83-36794#SOME APPLICATIONS OF ULTRASONIC METHODS FOR THEQUALITY CONTROL OF NONMETALLIC OBJECTS [WYBRANEZASTOSOWANIA METOD ULTRADZWIEKOWYCH DO OCENYJAKOSCI WYROBOW WYKONANYCH Z TWORZYWNIEMETALOWYCH]I AUERBACH, E NAPORA, W SZACHNOWSKI, and KSZCZEPANSKI Instytut Lotnictwa, Prace (ISSN 0509-6669), no91, 1982, p 73-87 In Polish

Two methods of nondestructive ultrasonic testing are describedwhich have been developed for the quality control of the rotorblades of the drive system of an agricultural aircraft and for thequality control of the adhesive joints of an aircraft undercarriageskid A procedure for optimizing the ultrasonic method is proposed,and the design of auxiliary equipment for production control isdiscussed B J

A83-36354#EFFECTS OF COMPRESSOR HUB TREATMENT ON STATORSTALL MARGIN AND PERFORMANCEP CHENG, M E PRELL, E M GREITZER, and C S TAN (MIT,Cambridge, MA) AIAA, SAE, and ASME, Joint PropulsionConference, 19th, Seattle, WA, June 27-29, 1983 9 p refs(Contract F49620-82-K-0002)(AIAA PAPER 83-1352)

The application of grooves or slots over the rotor tips in thecasing of an axial flow compressor can have a large effect oncompressor stall margmg and performance Relative motionbetween endwall and blade is found to be an important elementfor the success of the grooves in reducing the endwall boundarylayer blockage in the rotor tip region In this connection, thequestion has been asked whether a rotating 'hub treatment' belowa row of cantilevered stator blades would also be effective inimproving the stall margin The present investigation is concernedwith the effect of hub treatment on the stall margin and performanceof a 'hub critical' stator Two sets of bladmg configurations weretested, each with a solid wall and with hub treatment It wasfound that for the first set of bladmg (low stagger) the applicationof hub treatment did not have a major effect on the statorperformance However, for the second set of bladmg (high stagger),the hub treatment improved the compressor performance G R

A83-36405#FEASIBILITY OF DRY LUBRICATION FOR LIMITED-DUTY GASTURBINE ENGINESJ DILL (USAF, Aero Propulsion Laboratory, Wright-Patterson AFB,OH), D BRANDES, P KAMSTRA, and R SOLOMON (GarrettTurbine Engine Co, Phoenix, AZ) AIAA, SAE, and ASME, JointPropulsion Conference, 19th, Seattle, WA, June 27-29, 1983 14p DARPA-USAF-supported research refs(AIAA PAPER 83-1130)

The advantages and disadvantages of dry-lubrication systemsfor limited duty engines, those that are of only intermittent oremergency use, are discussed, together with technology areasneeding development to produce a dry lubricated turbine engineTwo approaches have been identified, one in which the lubricantis already in the bearing, the second involving an external feed tothe bearing Dry lubricated bearings have two critical materialproperties, thermal conductance and the thermal expansioncoefficient The materials must be resistant to oxidation andcorrosion Hot-pressed silicon nitride ceramics have demonstratedthe desired features, but at a high cost, with surface cleanlinessproblems, and some doubt is present as to their uniformity

A83-36910DETERMINATION OF THE SENSITIVITY OF U S. AIR FORCEAIRCRAFT HYDRAULIC SYSTEM COMPONENTS TOPARTICULATE CONTAMINATIONC E SNYDER, JR , L J GSCHWENDER, and C J PELLERIN(USAF, Wright Aeronautical Laboratories, Wright-Patterson AFB,OH) Lubrication Engineering (ISSN 0024-7154), vol 39, July1983, p 450-455, Discussion, p 455, 456, Authors' Closure, p456, 457

The effect of particulate contamination on aircraft hydraulicsystem components was determined using a 3000 psi hydraulicmultipass test stand equipped with a horizontal stabilator actuatorand hydraulic pump used in the F-4 hydraulic system The testfluid was MIL-H-5606 hydraulic fluid Particulate contamination wasintroduced into the system in the form of AC test dust and wasadded in incremental amounts while changing the actuator pistondither position for a total of nine piston positions with increasingcontamination Filtration was added to the stand late in theexperiment Fluid samples were drawn throughout the experimentand properties were monitored Both the actuator and the pumpwere monitored for leakage rates and the pump was monitoredfor outlet pressure during the experiment Post-test inspection ofthe hardware and fluid analyses lead to wear/contaminationconclusions which were relevant to Air Force aircraft operations

Author

N83-25919# Transportation Research and Marketing, Salt LakeCity, UtahTRANSPORTATION ENERGY CONSERVATION THROUGHLAND USE PLANNING Final ReportJun 1982 58 p refs Conf held in Washington, DC, 5-6Nov 1981 Sponsored in part by the FHA(PB83-148387, DOT-1-82-50) Avail NTIS HC A04/MF A01CSCL 13B

The interrelationships of transportation, land use and energyare covered Two major areas were highlighted, the fundamentalsocial, economic, energy, and cultural factors that influenceplanning, and opportunities for the coordination of transportationand land use Although no specific recommendations are contained,highlight examples of effective plans and programs and questionsthat can form the basis for further research are described GRA

475

12 ENGINEERING

N83-25929# National Severe Storms Lab , Norman, OklaSCANNING STRATEGIES FOR NEXT GENERATION WEATHERRADARS A STUDY BASED ON LIFETIMES OF CONVECTIVEATMOSPHERIC PHENOMENA HAZARDOUS TO AVIATION FinalReportP R MAHAPATRA and D S ZRNIC Jul 1982 94 p refs(Contract DTFA01-80-Y-10524)(FAA-RD-82-69) Avail NTIS HC A05/MF A01

The lifetimes of significant features in typical storm phenomenawere investigated and the results are expected to help in decidingthe scan strategy of NEXRAD radars In particular, the questionof the adequacy of a 5 minute information update rate for NEXRADin its aviation weather surveillance role was addressed Twomethods are used for the lifetime study photo-interpretive andcomputer based correlation The basis and program steps of thecorrelation method are discussed Several storms are studied usingboth methods It is found that the storms studied contain no featurethat might have been missed by a 5 minute scan cycle providedthat data from all the three moment fields (reflectivity, radial velocity,and Doppler spectrum width) at several elevations are utilized inthe detection of hazardous phenomena Author

N83-25938# Houston Univ, Tex Dept of ElectricalEngineeringTHE REMOTE LINK UNIT: A DEMONSTRATION OFOPERATIONAL PERFORMANCE. PART 2: USER'S MANUALFinal Report, 1 Apr. - 31 Dec 1980C J TAVORA, J R GLOVER, JR, M A SMITHER, H MCOLLINS, and W C LAW Wright-Patterson AFB, OhioAFWAL Aug 1981 113p refs 2 Vol(Contract F33615-80-C-1095, AF PROJ 2003)(AD-A124620, AFWAL-TR-81-1131-PT-2) Avail NTIS HCA06/MFA01 CSCL17B

The purpose of this manual is to provide a guide for the useand operation of the Remote Link Unit Demonstration System(RLUDS) without the details of the design of the system Thesections of this manual provide information on inspection of theequipment to verify a correct physical configuration, external cableconnections, procedures for operation This manual provides allthe details necessary for operations of the RLUDS, assuming theuser is generally knowledgeable of the concept, purpose, andconfiguration of the RLU and its major components Bothbackground information and design details may be found in theDesign Manual (Part III) GRA

N83-25934# Houston Univ, Tex Dept of ElectricalEngineeringTHE REMOTE LINK UNIT A DEMONSTRATION OFOPERATIONAL PERFORMANCE PART 3: DESIGN MANUAL,VOLUME 1 Final Report, 1 Apr. - 31 Dec. 1980C J TAVORA, J R GLOVER, JR , M A SMITHER, H MCOLLINS, and W C LAW Wright-Patterson AFB, OhioAFWAL Aug 1981 230 p refs 2 Vol(Contract F33615-80-C-1095, AF PROJ 2003)(AD-A124621, AFWAL-TR-81-1131-PT-3-VOL-1) Avail NTIS HCA11/MFA01 CSCL 17B

This document is a design manual for the Remote Link UnitDemonstration System (RLUDS) The Remote Link Unit (RLU) isa new design concept for remote terminals This document containsdetailed design information on the RLUDS The RLUDS describedin this design manual is an operational hardware breadboardprototype that performs most of the important RLU functions Thiseffort has demonstrated the feasibility of implementation of theLink Module (LM), the Interface Configuration Adapter (ICA), theElectronic Nameplate (NP) and the Interface between the LinkModule and the Link Manager The Link Manager (LMG) wassimulated with a PDP-11 computer The extent of RLUimplementation encompassed by the demonstration unit isillustrated The configuration of the RLUDS is presented GRA

N83-25935# Houston Univ, Tex Dept of ElectricalEngineeringTHE REMOTE LINK UNIT: A DEMONSTRATION OFOPERATIONAL PERFORMANCE. PART 3: DESIGN MANUAL.VOLUME 2: APPENDICES A - C Final Report, 1 Apr. - 31 Dec.1980C J TAVORA, J R GLOVER, JR, M A SMITHER, H MCOLLINS, and W C LAW Wright-Patterson AFB, OhioAFWAL Aug 1981 661 p refs 2 Vol(Contract F33615-80-C-1095, AF PROJ 2003)(AD-A124622, AFWAL-TR-81-1131-PT-3-VOL-2) Avail NTIS HCA99/MFA01 CSCL17B

The source code tape directory, hardware schematics, andsoftware flow charts are presented for the remote link unit GRA

N83-25939# Houston Univ, Tex Dept of ElectricalEngineeringTHE REMOTE LINK UNIT A DEMONSTRATION OFOPERATIONAL PERFORMANCE, PART 1 Final SummaryReport, 1 Apr - 31 Dec. 1980C J TAVORA, J R GLOVER, JR, M A SMITHER, H MCOLLINS, and W C LAW Wright-Patterson AFB, OhioAFWAL Aug 1981 36 p refs 2 Vol(Contract F33615-80-C-1095, AF PROJ 2003)(AD-A124619, AFWAL-TR-81 -1131 -PT-1) Avail NTIS HCA03/MFA01 CSCL 17B

This report summarizes the results of the program ofimplementation of an RLU Demonstration System This systemallows the evaluation of the most unique parts of the RLU andhas facilitated the resolution of problem areas in the RLU designEnhancements to the RLU functional design are presented andan implementation plan for an RLU prototype is proposed TheUser's Manual and the Design Manual for the system are includedas Parts II and III, respectively Author (GRA)

N83-25948# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringANALYSIS OF F-16 RADAR DISCREPANCIES M.S ThesisK A RICHE Dec 1982 44 p refs(AD-A124749, AFIT/GE/EE/82D-56) Avail NTIS HC A03/MFA01 CSCL 15E

One hundred and eight aircraft were randomly selected fromthree USAF F-16 bases and examined These aircraft included 63single-seat F-16As and 45 two-seat F-16Bs and encompassed8,525 sorties and 748 radar system write-ups Programs supportedby the Statistical Package for the Social Sciences (SPSS) wererun on the data Of the 748 discrepancies, over one-third of themoccurred within three sorties of each other and half within sixsorties Sixteen percent of all aircraft which had a discrepancywithin three sorties had another write-up within the next threesorties Designated repeat/recurring write-ups representedone-third of all the instances in which the write-up separationinterval was three sorties or less This is an indication thatmaintenance is unable to correct equipment failures as they occur,most likely because the false alarm rate is too high andmaintenance is unable to duplicate the error conditions on theground for correct error diagnosis GRA

476

12 ENGINEERING

N83-25990# Edgerton, Germeshausen and Gner, Inc, Salem,MassPHASE 2A BENCH MODEL DEVELOPMENT TACTICALRUBIDIUM FREQUENCY STANDARD Final Technical Report,16 Feb. - 16 Jun. 1982W J RILEY Hanscom AFB, Mass RADC Dec 1982 34 p(Contract F1628-81-C-0055, AF PROJ 2277)(AD-A124462, RADC-TR-82-253) Avail NTIS HC A03/MF A01CSCL 14B

A working bench model of a rubidium frequency standard hasbeen designed and built that offers small size, fast warm-up andruggedness for avionic applications Author (GRA)

N83-26023# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringDESIGN OF CHOKING CASCADE TURNS M.S. ThesisJ BAIRD Dec 1982 79 p refs(AD-A124792, AFIT/GAE/AA/82D-3) Avail NTIS HC A05/MFA01 CSCL 16D

Five different shock-positioning cascades, for short-radius turnsin ramjet inlet diffusers, were designed and tested on the AFITwater table These flow controllers were to perform the samefunction as the conventional arrangement of an aerodynamic gridand a long-radius turn The tests were to determine the suitabilityof the water table for such experimentation, in addition todetermining the flow-control capabilities and pressure recovery ofthe cascades All five designs accomplished the flow-controlfunction as designed, and two designs exhibited the same or betterpressure recovery than the aerodynamic grid The water tableproved to be an excellent means of testing these cascades,primarily due to the ease of flow visualization in the tests doneThe shock-positioning cascade, short-radius turn concept showspromise and should be tested further in gas-dynamic apparatus

Author (GRA)

N83-26080*# National Aeronautics and Space AdministrationMarshall Space Flight Center, Huntsville, AlaDAMPING SEAL FOR TURBOMACHINERY Patent ApplicationG L VONPRAGENAU, inventor (to NASA) 28 Apr 1983 11 p(NASA-CASE-MFS-25842-1, US-PATENT-APPL-SN-489902)Avail NTIS HC A02/MF A01 CSCL11A

A damping seal between a high speed rotor member and statormember that separates pressurized fluid compartments isdescribed The rotor member has a smooth outer surface and thestator member has a bore surface roughened by a plurality ofpockets or depressions NASA

N83-26099# Air Force Inst of Tech , Wright-Patterson AFB,Ohio School of EngineeringSTATIC AEROELASTIC ANALYSIS OF FLEXIBLE WINGS VIANASTRAN, PART 1 M. S. ThesisK JONES Dec 1982 97 p refs(AD-A124662, AFIT/GAE/AA/82D-16-PT-1) Avail NTIS HCA05/MF A01 CSCL 01C

The purpose of this study was to expand the capabilities ofthe Static Flexible Wing Aeroelastic Sequence that Captain LanceP Chrismger developed for NASTRAN as his Master's Thesis atAFIT Captain Chrismger developed a basic procedure to enableNASTRAN to analyze flexible wing airloads and stresses Thatcapability is expanded to enable analysis of standard wing modelsA subroutine was incorporated into NASTRAN to eliminateextensive hand-calculation of transformation matrices Thecapability to tolerate control surfaces was discovered Also, asurvey of wing models in the Air Force inventory was taken todetermine the characteristics of the average wing model Thiswas used to determine where the aeroelastic procedure was lackingin its ability to analyze wing models Author (GRA)

N83-26103# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringSTRUCTURAL MODEL TUNING VIA VECTOR OPTIMIZATIONM.S. ThesisC R DEVORE Dec 1982 82 p refs(AD-A124791, AFIT/GAE/AA/82D-8) Avail NTIS HC A05/MFA01 CSCL 13M

This report examines tuning a finite element model using vectoroptimization techniques Structural models using finite elementtheory often need to be adjusted so they can accurately simulatethe real structure The goal is to tune the model such that it willreproduce data derived from the structure The tuning procedureis complicated by many factors First of all, the model may berequired to reproduce several sets of different performance datawhich may have conflicting effects on the model The numberand kinds of parameters to modify may be large or uncertainAlso, there may be many constraints on the model With all theseconsiderations and several performances indices to extremize,there may be many compromise solutions to examine in order toselect the best one Therefore, the problem has been broken intotwo parts First, the performance indices are extremized usingmultiple objective optimization theory, producing a set of possiblesolutions Next, the solutions are ranked ordered according to adecision maker's preferences The solution ranked number oneis, then, the best answer The tuning process was applied to aT-38 horizontal stabilator Four static deformation and two naturalfrequency experimentally determined data sets were used as theobjective functions for the three parameter model GRA

N83-26081# Hughes Helicopters, Culver City, CalifULTRASONIC WELD BONDING OF HELICOPTER PRIMARYSTRUCTURES Final Report, Sep. 1979 - Jul. 1981K K NIJI Dec 1982 38 p refs(Contract DAAK51-79-C-0045)(AD-A124645, USAAVRADCOM-TR-82-D-28, HHI-82-261) AvailNTIS HC A03/MF A01 CSCL 13H

This program was a study to develop and optimize an ultrasonicweld bonding procedure for the fabrication of primary structuralcomponents for helicopters This procedure, a combination ofultrasonic welding and adhesive bonding, was studied through aseries of coupon tests Various adhesives and surface treatmentswere evaluated with regard to their adaptability of ultrasonic weldbonding Adhesive bond quality and weld quality were evaluatedthrough various T-shear, fatigue, and environmental salt-spray testsEnvironmental degradation of the adhesively bonded areasoccurred consistently and could not be resolved It was determinedthat the surface condition required for good adhesive bondingwas not compatible with that required for good ultrasonic weldingand the program was terminated Author (GRA)

N83-26805# Air Force Flight Dynamics Lab, Wright-PattersonAFB, OhioADVANCES IN EJECTOR TECHNOLOGY: A TRIBUTE TO HANSVON OHAIN'S VISION Final ReportK S NAGARAJA In AFWAL A Collection of Papers in theAerospace Sci p 489-517 Jun 1982 refsAvail NTIS HC A99/MF A01 CSCL 20D

A brief review of the significant accomplishments made at ARLin the basic understanding of the aerothermo fluid dynamiccharacteristics of ejectors is given The studies of AFFDL whichfurther enhanced the state-of-the-art of the ejectors for V/STOLapplications are also indicated The spectrum of activities in theAir Force not only gave a great deal of insight into thecharacteristics of the ejector flows, but also resulted in thedevelopment of compact ejectors that are relevant foor aircraftapplication The saga of ejector investigations is continuing and itis within the realm of possibility that ejector systems will besuccessfully applied for a variety of aircraft operations in the comingyears B W

477

12 ENGINEERING

N83-27114# Ecole Nationals Superieure desTelecommunications, Paris (France) Dept Systemes etCommunicationsNUMERICAL TREATMENT OF DOPPLER RADAR SIGNALSPh.D. Thesis [TRAITEMENT VIDEO DOPPLER EN RADAR]B GONULLU 17 Dec 1982 200 p refs In FRENCH(ENST-E-82014) Avail NTIS HC A09/MF A01

Doppler radar signal processing algorithms are discussed Theanalysis of a moving target identification filter system leads to afast Fourier transform implementation with a matrix of order eightThe analytic computation of the plot center, the estimation ofradial velocity, the logarithmic laws and the multiplication using aPROM table are discussed Applications of filters with distributedzeroes and of residium arthmetic are examined Author (ESA)

N83-27148*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifCALCULATION OF BOUNDARY LAYERS NEAR THESTAGNATION POINT OF AN OSCILLATING AIRFOILT CEBECI (California State Univ, Long Beach) and L W CARRMay 1983 17 p refs Prepared in cooperation with ArmyResearch and Technology Labs , Moffett Field, Calif(NASA-TM-84305, A-9143, NAS 1 1584305,USAAVRADCOM-TR-83-A-1) Avail NTIS HC A02/MF A01CSCL 20D

The results of an investigation of boundary layers close to thestagnation point of an oscillating airfoil are reported Twoprocedures for generating initial conditions, the characteristics boxscheme and a quasi-static approach, were investigated, and thequasi-static approach was shown to be appropriate provided theinitial region was far from any flow separation With initial conditionsgenerated in this way, the unsteady boundary layer equations weresolved for the flow in the leading edge region of a NACA 0012airfoil oscillating from 0 to 5 deg Results were obtained for bothlaminar and turbulent flow, and, in the latter case, the effect oftransition was assessed by specifying its occurrence at differentlocations The results demonstrate the validity of the numericalscheme and suggest that the procedures should be applied tocalculation of the entire flow around oscillating airfoils Author

N83-27149*# National Aeronautics and Space AdministrationAmes Research Center, Moffett Field, CalifIMPLICIT UPWIND METHODS FOR THE COMPRESSIBLENAVIER-STOKES EQUATIONST J COAKLEY May 1983 13 p refs Proposed for presentationat the AIAA Computational Fluid Dyn Conf, Danvers, Mass , 13-15Jul 1983(NASA-TM-84364, A-9332, NAS 1 1584364) Avail NTIS HCA02/MF A01 CSCL 20D

A class of implicit upwind differencing methods for thecompressible Navier-Stokes equations is described and appliedThe methods are based on the use of local eigenvalues or wavespeeds to control spatial differencing of inviscid terms and areaimed at increasing the level of accuracy and stability achievablein computation Techniques for accelerating the rate ofconvergence to a steady state solution are also used Applicationsto inviscid and viscous transonic flows are discussed and comparedwith other methods and experimental measurements It is shownthat accurate and efficient transonic airfoil calculations can bemade on the Cray-l computer in less than 2 mm Author

N83-27210# Research Inst of National Defence, Lmkoepmg(Sweden) Dept 3LASER SAFETY OF AIR BATHYMETRYB KLEMAN Jan 1983 26 p refs In SWEDISH, ENGLISHsummary(FOA-C-30292-E1) Avail NTIS HC A03/MF A01

Data for permissible irradiation at pulse-repetition green N dYAG radiation are reported Flight altitude and speed permissiblefor irradiation at the sea surface are discussed Safety aspects oflaser bathymetry from helicopters or aircraft are treated The needfor the laser operator to have observational control over the partof the sea surface that can be hit by radiation of higher irradiance

than the threshold value is stressed The risks of flights overislands and shores are outlined, as well as the risks for animallife Author (ESA)

N83-27213*# Rocketdyne, Canoga Park, CalifHYBRID HYDROSTATIC/BALL BEARINGS IN HIGH-SPEEDTURBOMACHINERY Final Report, 29 Aug. 1980 - 15 Dec.1982C E NIELSON Jan 1983 381 p refs(Contract NAS3-22480)(NASA-CR-168124, NAS 126 168124, RI/RD83-104) AvailNTIS HC A17/MF A01 CSCL 131

A high speed, high pressure liquid hydrogen turbopump wasdesigned, fabricated, and tested under a previous contract Thisdesign was then modified to incorporate hybrid hydrostatic/ballbearings on both the pump end and turbine end to replace theoriginal conventional ball bearing packages The design, analysis,turbopump modification, assembly, and testing of the turbopumpwith hybrid bearings is presented here Initial design considerationsand rotordynamic performance analysis was made to defineexpected turbopump operating characteristics and are reportedThe results of testing the turbopump to speeds of 9215 rad/s(88,000 rpm) using a wide range of hydrostatic bearing supplypressures are presented The hydrostatic bearing test data andthe rotordynamic behavior of the turbopump was closely analyzedand are included in the report The testing of hybrid hydrostatic/ballbearings on a turbopump to the high speed requirements hasindicated the configuration concept is feasible The program haspresented a great deal of information on the technologyrequirements of integrating the hybrid bearing into high speedturbopump designs for improved bearing life Author

N83-27260# Air Force Inst of Tech, Wright-Patterson AFB,OhioANALYSIS OF PROGRESSIVE COLLAPSE OF COMPLEXSTRUCTURES Ph.D. ThesisG E RIGGS Dec 1982 205 p refs(AD-A125266, AFIT-CI-NR-82-63D) Avail NTIS HC A10/MFA01 CSCL 12A

The principal goal of the study was to evaluate an analyticalprocedure for predicting progressive collapse in damaged complexstructures A structure was modeled for analysis by the finiteelement method using relatively large, simple elements There waslittle or no refinement of mesh size in areas of initial damage ordamage propagation A method was developed for determiningand applying allowable stresses to help compensate for theabsence of model detail Stress results of a finite element analysiswere examined by a computer post-processor program written forthis study to make selective changes to the finite element modelThe modified model was analyzed using the finite element methodand the procedure was repeated in an iterative fashion to predictprogressive collapse Analytical results were compared toexperimental test data to determine the validity of the analyticalprocedure The analytical procedure provided a relativelyeconomical method for predicting progressive collapse in a complexstructure Evaluation of a complex structure subjected to threeinitial damage conditions showed acceptable correlation betweenexperimental and analytical results The method of determiningappropriate allowable stresses was general enough to apply to awide range of materials and structures The procedure proved tobe an economical estimating tool for predicting residual structuralstrength Author (GRA)

478

13 GEOSCIENCES

13

GEOSCIENCES

Includes geosciences (general), earth resources, energy productionand conversion, environment pollution, geophysics, meteorologyand climatology, and oceanography

N83-26320# Mitre Corp , McLean, VaFAA INTEGRATED NOISE MODEL VALIDATION: ANALYSISOF AIR CARRIER FLYOVERS AT SEATTLE-TACOMAAIRPORTG W FLATHERS, II Washington FAA Nov 1982 73 prefs(Contract DTFA01-82-C-10003)(AD-A124097, FAA-EE-82-19, MTR-82W162) Avail NTIS HCA04/MF A01 CSCL 09B

The Federal Aviation Administration's Integrated Noise Model(INM) is a series of computer programs designed to estimateenvironmental noise levels in the vicinity of an airport As part ofthe effort's to validate INM outputs for the FAA, comparisonswere made between the Sound Exposure Levels (SEL) of actualaircraft flyovers at Seattle-Tacoma International Airport and SELswhich were computed by the INM for identical conditions Datafor this analysis were obtained from the FAA ARTS-MI radar todetermine the actual slant range and velocity of observed aircraft,and from noise monitors located beyond each runway end todetermine actual SEL values associated with observed aircraftThe report presents the results of the comparison of INM andobserved SEL values for seven transport-category aircraft GRA

N83-26322/ Federal Aviation Administration, Washington, DCOffice of Environment and EnergyA SURVEY OF HELICOPTER AND AMBIENT URBAN NOISELEVELS IN PHOENIX, ARIZONA Final ReportJ S NEWMAN Sep 1982 44 p(AD-A123856, FAA-EE-82-20) Avail NTIS HC A03/MF A01CSCL 20A

The FAA has been conducting controlled helicopter noisemeasurement programs since 1976 The data have been used fora variety of purposes including evaluation of proposed U S andinternational noise standards, validation of helicopter noiseprediction methodologies, and development of practical heliportdesign guidance In order to supplement the results of the controlledtests, field survey data are also being gathered to representin-service operating conditions Measurements are intended torepresent helicopter noise within the context of urban ambientbackground noise The results reported in this document are termed'survey measurements', as opposed to controlled test data, inorder to reflect the limited control imposed over factors whichcontribute to the variability of measured noise levels Noise dataare presented for the Bell 206-L, Aerospatiale Alouette III, andthe Aerospatiale A-Stare, SA-350 Operational modes includeapproach, takeoff, hover, and flat-pitch-idle Noise data includeA-weighted Sound Level time histories, maximum A-WeightedSound Level (LASm), Sound Exposure Level (LAE), and EquivalentSound Level (Leq) Author (GRA)

NS3-26345# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringA REVIEW AND COMPARISON OF LIGHTNING RETURNSTROKE MODELS USING EXPERIMENTAL DATA M S. ThesisS M HANIF Dec 1982 182 p refs(AD-A124680, AFIT/GE/EE/82D-61) Avail NTIS HC A09/MFA01 CSCL 12A

Over the last three decades many lightning return stroke modelshave been proposed to predict the current pulse of the returnstroke as it propagates in the channel These models were mainlyproposed by trying to solve the inverse problem of suggesting thecurrent in the channel which will give the experimentalmeasurement of the electromagnetic (EM) fields on the ground

Due to the lack of airborne data, the validity of these models asa function of height have not been verified In this thesis weprovide a discussion of all the significant return stroke modelsand their credibility as a function of height by comparing their EMfields with recent acquired airborne lightning data The equationsto compute the electric and magnetic fields in space due to avertical channel are also derived The last part of the thesis isrelated to the comparison of these models The predicted fieldsdue to Master et al were plotted and compared with the empiricalresults Also, the Master et al model was modified for the channelcurrent pulse propagation velocity and the channel current waveform The plots due to these modifications are included andcompared with the experimental data GRA

N83-26367# Air Force Geophysics Lab, Hanscom AFB, MassMeteorology DivANALYSIS AND SPECIFICATION OF SLANT WIND SHEARInterim ReportH A BROWN 8 Nov 1982 44 p refs(AD-A125883, AFGL-TR-82-0366, ERP-810) Avail NTIS HCA03/MF A01

Wind data collected at the Air Force Geophysics Laboratory(AFGL) Otis Weather Test Facility (WTF) for the period 28 March1981 to 4 May 1981 have been analyzed to produce frequenciesof occurrence of slant wind shear with respect to surface windspeed, time of day, vertical temperature gradient and wind sheardirection differences Slant wind shear (SWS) is a measurementthat more closely approximates the shear encountered by anaircraft on takeoff or landing It is computed as the wind shearbetween a higher level wind (in this study, 60 m) and the surfaceseparated by a horizontal distance equivalent to that which anaircraft would traverse in descending or ascending that height

BW

N83-27476# Techmsche Hogeschool, Delft (Netherlands) Deptof Aerospace EngineeringAERODYNAMIC RESEARCH ON TIPVANE WINDTURBINESG J W VANBUSSEL, T VANHOLTEN, and G A M VANKUIKApr 1982 19 p refs(PB83-147413, LR-355) Avail NTIS HC A02/MF A01 CSCL10B

The research on tipvane turbines aims at a processimprovement of the wind energy conversion system, which is morethan component improvement such as efficient aerofoils andoptimized transmission systems These latter developments makeit possible for a modern wind turbine to approach the Betz maximumpower coefficient However, process improvements are possiblebased on flow phenomena which are not consistent with theassumptions made in Betz theory Power coefficients far abovethe Betz maximum value are possible when for example forcesare applied perpendicular to the winddirection and when viscouseffects play an important role The effect of tipvanes, which aresmall auxiliary wings at the end of the turbine blades inducing amass flow augmentation by the creation of a ventun flow isinvestigated GRA

N83-27537*# National Aeronautics and Space AdministrationGoddard Space Flight Center, Greenbelt, MdRF RADIATION FROM LIGHTNING CORRELATED WITHAIRCRAFT MEASUREMENTS DURING STORM HAZARDS-82D M LEVINE Mar 1983 27 p refs(NASA-TM-85007, NAS 1 1585007) Avail NTIS HC A03/MFA01 CSCL 04B

During the Storm Hazards Experiment 1982, the Goddard SpaceFlight Center monitored radiation from lightning from a site at theWallops Flight Facility, Wallops Island, VA Measurements weremade while the NASA F106 penetrated thunderstorms to obtaindata on lightning strikes to the aircraft The objective of theground-based measurements was to help determine if the eventsrecorded by the F106 were part of lightning discharges Duringthe experiment, 53 cases were obtained in which events wererecorded aboard the aircraft while reliable quality RF radiationwas recorded on the ground These cases came from 12 different

479

15 MATHEMATICAL AND COMPUTER SCIENCES

storms occurring from June through August 1982 The data confirmsthat the aircraft was measuring events which were part of lightningand indicates that the events recorded on the aircraft tend tooccur early in the flash Author

15

MATHEMATICAL AND COMPUTER SCIENCES

Includes mathematical and computer sciences (general), computeroperations and hardware, computer programming and software,computer systems, cybernetics, numerical analysis, statistics andprobability, systems analysis, and theoretical mathematics

A83-33613SURFACES IN COMPUTER AIDED GEOMETRIC DESIGN;PROCEEDINGS OF THE CONFERENCE, OBERWOLFACH,WEST GERMANY, APRIL 25-30, 1982R E BARNHILL, ED (Utah, University, Salt Lake City, UT) andW BOEHM (Braunschweig, Technische Universitaet, Brunswick,West Germany) Amsterdam, North-Holland Publishing Co , 1983,231 p

Aspects of computer aided surface representation and designare considered along with a method of constructing nonstandardsurface patches, methods and applications of the mathematicalcurve and surface description in the case of passenger cardevelopment, questions concerning a smooth interpolation toscattered three-dimensional data, and the continuity of curvaturebetween adjacent Bezier patches Other topics considered arerelated to the generation of the Bezier points of triangular splines,some aspects of car body design in a German automobile factory,convex combination surfaces, the de Boor algorithm for triangularsplines, the design and fairing of ship surfaces, and surfaceapproximation with imposed conditions Attention is also given todual Bezier curves and surfaces, surfaces and their applicationsas used by a German car manufacturer, surface construction basedupon tnangulation, the construction of functions for therepresentation of surfaces, and multivanate splines G R

A83-36210#SINUSOIDAL INTEGRATION FOR SIMULATION OFSECOND-ORDER SYSTEMSD R ROLSTON (McDonnell Aircraft Co, St Louis, MO) INFlight Simulation Technologies Conference, Niagara Falls, NY, June13-15, 1983, Collection of Technical Papers New York, AmericanInstitute of Aeronautics and Astronautics, 1983, p 52-63 refs(AIAA PAPER 83-1086)

Many classical numerical methods for differential equations arebased on the exact integration of polynomial functions However,methods based on sinusoidal functions may be better suited toanalysis of oscillatory systems Discrete time difference equationshave been developed for sinusoidal extrapolation, predictorintegration, and corrector integration and tested in the equationsof motion of real-time flight simulation The computational stabilityand accuracy were significantly improved when a sinusoidal functionfrequency was chosen to match the natural frequency of theaircraft Author

A83-36212#ANALYSIS OF A REAL-TIME APPLICATIONR SHASTRI (Gould, Inc, S E L Computer Systems Div, FortLauderdale, FL) IN Flight Simulation Technologies Conference,Niagara Falls, NY, June 13-15, 1983, Collection of Technical Papers

New York, American Institute of Aeronautics and Astronautics,1983, p 71-74(AIAA PAPER 83-1088)

In most real-time applications such as simulation and processcontrol, the scope of the project at its onset is usually muchsmaller than what it turns out to be downstream into the projectAs the project progresses, additional requirements are specified

and a situation is reached wherein the programs expand toconsume all available compute power and/or resources This paerdescribes the characteristics of a real-time application in the fieldof simulation and process control, explores the nature of theproblem and suggests some implementation considerations thatshould be adapted in the initial design phase In doing so,down-the-hne enhancements are readily accommodated and, ifnecessary, resources may be added incrementally, such that thesystem as a whole never reaches a performance or resourcethreshold Author

A83-36223#OLD PROBLEM/NEW SOLUTIONS - MOTION CUINGALGORITHMS REVISITEDF M CARDULLO (New York, State University, Bmghamton, NY)and R L KOSUT (Integrated Systems, Inc , Palo Alto, CA)American Institute of Aeronautics and Astronautics, FlightSimulation Technologies Conference, Niagara Falls, NY, June13-15, 1983 8 p refs(AIAA 83-1082)

The design concept of a nonlinear cue-shaping filter to exploitthe motion-system-hardware capability of flight simulators ispresented Cue-error and sensory-error expressions are derivedfrom the models of platform, aircraft, and sensory dynamics andinserted as parameters in a cost functional for theoptimal-tracking-control problem The resulting nonlinear filters areshown to be indirectly sensitive to cue magnitude, increasing onsetduration and washout-to-onset cue magnitude as input cuemagnitude decreases The approach used is seen as applicableto simulators incorporating other cues such as visual displays,g-seats, or vibration systems T K

A83-36430#INTERACTIVE FINE-TUNING OF LINEAR-QUADRATICGOVERNERS BY SELECTIVE AND DIRECT ACTION ON THEPOLES OF THE CONTROL SYSTEM [MISE AU POINTINTERACTIVE DES REGULATEURSLINEAIRES-QUADRATIQUES PAR ACTION DIRECTE ETSELECTIVE SUR LES POLES DU SYSTEME CONTROLE]O L MERCIER (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seme,France), Y JOANNIC, and O MOREIGNE (ONERA,Chatillon-sous-Bagneux, Hauts-de-Seme, Institut Industrie! du Nordde la France, Villeneuve d'Ascq, France) (International Associationof Science and Technology for Development, Symposiumd'lnformatique Applique, Lille, France, Mar 15-17, 1983) ONERA,TP, no 1983-21, 1983, 7 p In French refs(ONERA, TP NO 1983-21)

Interactive software for fine-tuning linear-quadratic governersfor use in engineering the control of optimal multivanable gains ispresented Analytical relationships are defined for characterizingthe response of the control system to variations in a specifiedvalue corresponding to the variation of a system parameter Theresulting response gradients account for cause-effect relationsexisting between the fitted values and the coefficients of theweighting matrices for the cost function The algorithm permitsqualitatively setting the end-points of a system's performance, i e ,use of the nondiagonal coefficients of the Q matrix that definesthe degrees of freedom of the system Furthermore, interactionbetween the machine and the operator is provided An exampleis provided of the case of multivanable piloting of an aircraft, andother aerospace applications are indicated M S K

A83-36455A MODIFIED ALGORITHM FOR DETERMINING STRUCTURALCONTROLLABILITYC R BURROWS and M N SAHINKAYA (Strathclyde, University,Glasgow, Scotland) International Journal of Control (ISSN0020-7179), vol 37, June 1983, p 1417-1431 Research supportedby the Science and Engineering Research Council refs

The algorithm of Burrows and Sahinkaya (1981) for determiningthe structural controllability of multi-input time invariant processeswith ill-defined parameter values is modified to take account ofinsights arising from an examination of three counter-examples

480

16 PHYSICS

The modified algorithm has the same underlying philosophy asthe original method It can be applied without computational aidsto determine the controllability of many practical problems andthis is demonstrated by examining a twelth order model of arotor-bearing system The method also provides an aid to systemdesign A graphical procedure is presented for determining therank of the pair (A, b) The extension to multiple inputs isdiscussed Author

N83-26501* Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringDEVELOPMENT OF AN OCULOMETER DATA COLLECTIONSUBSYSTEM M.S. ThesisN L WOOD Dec 1982 259 p refs(AD-A124700, AFIT/GE/EE/82D-72) Avail NTIS HC A12/MFA01 CSCL 09B

A SYM-1 microprocessor with dual 5-1/4 inch disk drives wasused to develop software to gather and reduce data from aCubic-Foot Remote Oculometer built by Honeywell, Inc The primaryfunction of the oculometer is to measure the look direction of apilot's eye in a ground cockpit simulator The output of theoculometer used for this effort is eye lookpoint in azimuth andelevation and whether the oculometer is tracking the eye or notThe hne-of-sight measurement covers a viewing field of plus andminus 30 degrees in azimuth and zero to plus 30 degrees inelevation This viewing field is broken into instruments whoseboundaries are defined by the data collection subsystemPerformance measures are printed out at the end of the datamission The software for the SYM-1 was developed modularlywith each module tested separately and then the whole subsystemtested Simulated oculometer data was used to test the softwareThe data collection subsystem was designed to run with minimalknowledge and interaction required by the user GRA

N83-26637# Air Force Inst of Tech, Wright-Patterson AFB,Ohio School of EngineeringAN INTERACTIVE BOMBING MISSION SIMULATION WITHCOMPUTER GRAPHICS INTERFACE M.S. ThesisM J GOCI Dec 1982 151 p refs(AD-A124661, AFIT/GCS/MA/82D-4) Avail NTIS HC A08/MFA01 CSCL 09B

An interactive flight simulation with computer graphics interfacewas designed using top-down structured analysis techniques Theproject converts a passive bombing mission simulation used inthe Avionics Laboratory, Air Force Wright Aeronautical Laboratoriesat Wright-Patterson AFB, into an interactive, real-time, man-m-loopsimulation The design was documented using SofTech's StructuredAnalysis and Design Technique (SADT) then coded in FORTRANThe graphics were implemented using TEKTRONIX PLOT-10software and the system operates on a VAX-11/780 computercoupled through a TEKTRONIX 4016 terminal Author (GRA)

N83-27624# Naval Postgraduate School, Monterey, CalifHAND-HELD COMPUTER PROGRAMS FOR PRELIMINARYHELICOPTER DESIGN M.S. ThesisP J FARDINK Oct 1982 180 p refs(AD-A125036) Avail NTIS HC A09/MF A01 CSCL 09B

This proiect gives the user of the HP-41 handheld programmablecalculator a series of programs that give acceptable results duringthe preliminary phases of the helicopter design process The projectconsists of three parts The first part consists of several shortprograms and their subroutine form These programs andsubroutines compute density altitude, density, disc area, solidity,tip velocity, induced velocity, coefficient of thrust, tip loss factor,equivalent chord, and ground effect The second part consists ofmajor subroutines These subroutines compute profile power,induced power, climb power, parasite power, and total power,equivalent area and induced power for tandem rotor, and datainput and change The third part consists of the main programsThese programs compute the various power requirements forhovering flight, forward (straight and level), flight, vertical flight,and foward climbing flight, also tail rotor power, autorotative flight,and tandem rotor flight GRA

16

PHYSICS

Includes physics (general), acoustics, atomic and molecularphysics, nuclear and high-energy physics, optics, plasma physics,solid-state physics, and thermodynamics and statistical physics

A83-33486*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioACOUSTIC MODAL ANALYSIS OF A FULL-SCALE ANNULARCOMBUSTORA M KARCHMER (NASA, Lewis Research Center, Cleveland,OH) American Institute of Aeronautics and Astronautics,Aeroacoustics Conference, 8th, Atlanta, GA, Apr 11-13, 1983 17p refs(AIAA PAPER 83-0760)

An acoustic modal decomposition of the measured pressurefield in a full scale annular combustor installed in a ducted testrig is described The modal analysis, utilizing a least squaresoptimization routine, is facilitated by the assumption of randomlyoccurring pressure disturbances which generate equal amplitudeclockwise and counter-clockwise pressure waves, and theassumption of statistical independence between modes Theseassumptions are fully justified by the measured cross spectralphases between the various measurement points The resultantmodal decomposition indicates that higher order modes composethe dominant portion of the combustor pressure spectrum in therange of frequencies of interest in core noise studies A secondmajor finding is that, over the frequency range of interest, eachindividual mode which is present exists in virtual isolation oversignificant portions of the spectrum Finally, a comparison betweenthe present results and a limited amount of data obtained in anoperating turbofan engine with the same combustor is made Thecomparison is sufficiently favorable to warrant the conclusion thatthe structure of the combustor pressure field is preserved betweenthe component facility and the engine Previously announced inSTAR as N83-21896 Author

A83-33487*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioCROSS SPECTRA BETWEEN TEMPERATURE AND PRESSUREIN A CONSTANT AREA DUCT DOWNSTREAM OF ACOMBUSTORJ H MILES, C A WASSERBAUER, and E A KREJSA (NASA,Lewis Research Center, Cleveland, OH) American Institute ofAeronautics and Astronautics, Aeroacoustics Conference, 8th,Atlanta, GA, Apr 11-13,1983 27 p refs(AIAA PAPER 83-0762)

The feasibility of measuring pressure temperature cross spectraand coherence and temperature-temperature cross spectra andcoherence at spatially separated points along with pressure andtemperature auto-spectra in a combustion rig was investigatedThe measurements were made near the inlet and exit of a 644m long duct attached to a J-47 combustor The fuel used was JetA The cross spectra and coherence measurements show thepressure and temperature fluctuations correlate best at lowfrequencies At the inlet the phenomena controlling the phaserelationship between pressure and temperature could not beidentified However, at the duct exit the phase angle of the pressureis related to the phase angle of the temperature by the convectedflow time delay Previously announced in STAR as N83-23116

MG

481

16 PHYSICS

A83-33505FULL-SCALE MEASUREMENTS OF BLADE-VORTEXINTERACTION NOISED A BOXWELL and F H SCHMITZ (U S Army, AeromechanicsLaboratory, Moffet Field, CA) American Helicopter Society, Journal(ISSN 0002-8711), vol 27, Oct 1982, p 11-27 refs

Full-scale far-field acoustic data on four different two-bladedrotors encountering blade-vortex interaction are compared TheUH-1H helicopter was tested with its standard NACA 0012 airfolrotor Data are also presented for the AH-1S helicopter configuredwith its standard 540 rotor, the Kaman K747 rotor, and the OGEEtip rotor The data were reduced using 'time-windowing' of theimpulsive noise event, thus enhancing the signal-to-noise ratio ofthe in-flight data Strong pressure gradients, isolated in the UH-1Hand AH-1S 540 rotor signatures, strongly influenced the subjectiveannoyance of the rotor The peak amplitudes and power spectrumof the K747 and OGEE rotors were about equal and generatedless annoyance than the standard AH-1S or UH-1H rotors

Author

N83-26643*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioA COMPACT INFLOW CONTROL DEVICE FOR SIMULATINGFLIGHT FAN NOISEL HOMYAK, J G MCARDLE, and L J HEIDELBERG 198311 p refs Presented at the 8th Aeroacoustics Conf, Atlanta,11-13 Apr 1983, sponsored by AIAA Previously announced inIAA as A83-28005(NASA-TM-83349, E-1606, NAS 1 1583349, AIAA-83-0680)Avail NTIS HC A02/MF A01 CSCL 20A

Inflow control device (ICD's) of various shapes and sizes havebeen used to simulate inflight fan tone noise during ground statictests A small, simple inexpensive ICD design was optimized fromprevious design and fabrication techniques This compacttwo-fan-diameter ICD exhibits satisfactory acoustic performancecharacteristics without causing noise attenuation or redirection Inaddition, it generates no important new noise sources Designand construction details of the compact ICD are discussed andacoustic performance test results are presented Author (IAA)

A83-35712THE RELATIONSHIP BETWEEN THE AERODYNAMIC ANDACOUSTIC CHARACTERISTICS OF COAXIAL JETS [O SVIAZIAERODINAMICHESKIKH I AKUSTICHESKIKHKHARAKTERISTIK SOOSNYKH STRUI]V M KUZNETSOV, M P LAVRUKHINA, and G MUNINAkademna Nauk SSSR, Izvestiia, Mekhamka Zhidkosti i Gaza (ISSN0568-5281), Mar-Apr 1983, p 124-128 In Russian refs

The results of an experimental study of the mean and peakvelocity distributions in the mixing zone of isothermal coaxial jetsare presented for jets with both regular and inverted velocity profiles(in the latter case the velocity of the outer flow exceeds that ofthe inner flow) Based on experimental results, estimates areobtained for the noise of coaxial jets with different initial profilevelocities These estimates are then compared with experimentalacoustic data V L

A83-36077#EDGE TONES IN HIGH-SPEED FLOWS AND THEIRAPPLICATION TO MULTIPLE-JET MIXINGA KROTHAPALLI, K KARAMCHETI, Y HSIA, and D BAGANOFF(Stanford University, Stanford, CA) AIAA Journal (ISSN0001-1452), vol 21, July 1983, p 937, 938(Contract F49620-79-0189)


N83-27793*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioJT150 1/2-SCALE NOZZLE JET NOISE EXPERIMENT ANDCOMPARISON WITH PREDICTIOND E GROESBECK and C A WASSERBAUER May 1983 26p refs(NASA-TM-83370, E-1636, NAS 1 1583370) Avail NTIS HCA03/MF A01 CSCL 20A

As part of a program to study flight effects on the exhaustnoise of a full scale JT15D engine, static half scale model jetnoise experiments were conducted Acoustic data were recordedfor microphone angles of 45 deg to 155 deg with jet conditionsfor the model scale nozzle corresponding closely to those at 55,73 and 97 percent of corrected rated speed for the full scaleengine These data are useful for determining the relativeimportance of jet and core noise in the static full scale enginetest data and will in turn allow for a proper evaluation of flighteffects on the exhaust noise results The model scale data arealso compared with he coaxial jet noise prediction Above 1000Hz, the prediction is nominally 0 to 3 dB higher than the dataThe arithmetic mean of the differences between the experimentalOASPL and the predicted OASPL for all angles for each run rangedfrom 0 to -3 2 dB The standard deviation of all the OASPLdifferences is 2 2 dB The discrepancies are greatest at low primaryjet velocities and appear to be due to inadequacy in the variablejet density exponent incorporated in the prediction procedure

SL

A83-36096*# Santa Clara Univ , CalifDERIVATION OF THE FUNDAMENTAL EQUATION OF SOUNDGENERATED BY MOVING AERODYNAMIC SURFACESH R AGGARWAL (Santa Clara, University, Santa Clara, CA) AIAAJournal (ISSN 0001-1452), vol' 21, July 1983, p 1048-1050refs(Contract NCC2-191)

Ffowcs Williams and Hawkings (1969) based their derivationof the fundamental equation of the sound generated by arbitrarilymoving aerodynamic surfaces on the study of mass and momentumbalance of a control volume imbedding a mathematical surface(s)exactly corresponding to real surface(s) These investigators alsosketched an alternative method, employing generalized functions,for its derivation This latter method, which was later developedby Farassat (1975), is purely mathematical and formal Goldstein(1976) used the free-space Green function to produce an implicitderivation of the Ffowcs Williams and Hawkings equation In thestudy presented here, Lowson's (1965) concept of moving pointsingularities is generalized to moving surface singularities, and anew derivation is given of the fundamental equation The derivationis based on topological considerations of the underlying space,the fluid medium, and the integral properties of the Dirac deltafunction C R

N83-27794*# National Aeronautics and Space AdministrationLewis Research Center, Cleveland, OhioLOW FLIGHT SPEED ACOUSTIC RESULTS FOR ASUPERSONIC INLET WITH AUXILIARY INLET DOORSR P WOODWARD, F W GLASER, and J G LUCAS 198247 p refs Presented at the 19th Joint Propulsion Conf, Seattle,Wash , 27-29 Jun 1983, sponsored by AIAA, SAE, and ASME(NASA-TM-83411, E-1694, NAS 1 15 83411) Avail NTIS HCA03/MF A01 CSCL 20A

A model supersonic inlet with auxiliary inlet doors and boundaylayer bleeds was acoustically tested in simulated low speed flightup to Mach 0 2 in the NASA Lewis 9x15 Anechoic Wind Tunneland statically in the NASA Lewis Anechoic Chamber A JT8Drefan model was used as the noise source Data were also takenfor a CTOL inlet and for an annular inlet with simulated centerbodysupport struts Inlet operation with open auxiliary doors increasedthe blade passage tone by about 10 dB relative to the closeddoor configuration although noise radiation was primarily throughthe mam inlet rather than the doors Numerous strong spikes inthe noise spectra were associated with the bleed system, andwere strongly affected by the centerbody location The supersonicinlet appeared to suppress multiple pure tone (MPT) generationat the fan source Inlet length and the presence of support strutswere shown not to cause this MPT suppression Author

482

16 PHYSICS

N83-27796# Pennsylvania State Univ , University Park AppliedResearch LabINVESTIGATION OF THE COUPLING OF UNSTEADY LIFT TOLOW ORDER ACOUSTIC DUCT MODES IN AN AXIAL FLOWFAN M.S. ThesisJ P COWAN 17 Jun 1982 145 p refs(Contract N00024-79-C-6043)(AD-A124819, ARL/PSU-TM-82-137) Avail NTIS HC A07/MFA01 CSCL 20A

By using flow distortion screens, the plane wave (0,0) and firsthigher order (-1,0) and (1,0) spinning modes were generated in alow-speed axial flow fan The perpendicular unsteady lift force ona segment of a nme-bladed rotor and the acoustic pressure alongthe duct were measured simultaneously by a strain gage sensorand a flush-mounted microphone, respectively The total pressurefield downstream of the screens was measured by circumferentiallytraversing a Kiel probe The typical signal-to-noise ratio wassufficiently high for the desired signal isolation with a spectrumanalyzer A phase-locked ensemble averaging technique was usedto obtain amplitude and phase measurements of the periodicunsteady signals Standing waves set up in the duct between therotor and duct inlet seemed to cause a back-reaction effect whichresulted in an increase and reduction of the unsteady lift forceabove and below expected levels If these effects are taken intoaccount, theoretical predictions coupling unsteady lift to acousticfar field pressure levels conform to measured data Therefore, itis concluded that there is a definite coupling between unsteadylift and acoustic pressure in the duct, yet determination of anunambiguous coupling factor would require more extensive dataacquisition GRA

N83-27801# Flying Training Wing (323d), Mather AFB, CalifEnvironmental Planning SectAICUZ (AIR INSTALLATION COMPATIBLE USE ZONE) REPORTProgress Report, 5 Jan. 1978 - Aug. 1982Sep 1982 103 p(AD-A124974) Avail NTIS HC A06/MF A01 CSCL 20A

The development and use of lands near U S Air Force baseis of continuing concern to Air Force officials It is recognized thatthe public must be protected from noise and other hazards of airbase operations At the same time it is recognized that landsnear air bases often are highly attractive areas for developmentAircraft operations are likely to continue from Mather AFB for theindefinite future Operations will include the T-37, T-43, B-52,KC-135 or replacement aircraft The types of aircraft, flight tracks,frequency, and other characteristics will be continuously evaluatedby Mather AFB to determine the effects on the AICUZ and thecommunity The AICUZ study was prepared to promote orderlyand compatible land use around Mather AFB Land use guidelinesand noise measurement techniques are based on recenttechnology Data from this study should be considered forincorporation into existing land use plans and ordinances ofsurrounding communities, and used as a basis for decisions onfuture land development requests GRA

N83-27803# Sandia Labs , Albuquerque, N Mex Facility SystemsEngineering DivSANDIA HELICOPTER ACOUSTIC DETECTOR (SHAD)H D ARLOWE May 1982 12 p refs(Contract DE-AC04-76DP-00789)(DE82-018925, SAND-81-0538) Avail NTIS HC A02/MF A01

The Sandia Helicopter Acoustic Detector was developed toprovide a low cost alternative to radar for countering the helicopterthreat at new DOE facilities The mam buildings of these newdesigns are generally hardened to provide significant delay to ahelicopter borne adversary team Under these circumstances thesensor is only required to detect helicopters that are in their finallanding phase and at close range (less than 75 m) This shortdetection range allows the use of a fairly simple acoustic detectionalgorithm without making the system overly sensitive to wind noise,motor vehicles, and ventilation/heat exchange blowers This workwas sponsored by the Department of Energy/Office of Safeguards

and Security as part of the overall Sandia Fixed Facility PhysicalProtection Program DOE

N83-27845*# Spectron Development Labs, Inc , Costa Mesa,CalifFEASIBILITY STUDY OF THREE-DIMENSIONAL HOLOGRAPHICINTERFEROMETRY FOR AERODYNAMICS Final ReportJ E CRAIG May 1983 64 p refs(Contract NAS2-19573)(NASA-CR-166483, MAS 1 26166483) Avail NTIS HC A04/MFA01 CSCL 20F

Laser holographic interferometry was tried as a nonmtrusivediagnostic tool for studying unsteady two dimensional flows ANACA 0012 airfoil was tested, while undergoing dynamic stall,over a range of Mach numbers of 0 3 to 0 5, Reynolds number of0 5 x 10 to the 6th power to 2 x 10 to the 6th power, and atreduced frequencies of 0015 to 015 It was found that bothquantitative and qualitative data could be obtained by the techniqueSurface pressures on the airfoil can be measured to within 1 % ofthose measured with orifices and pressure transducers when theflow is attached Velocity profiles were measured near the wakeregion, and they compared very well with laser velocimeter datafor attached flows For separated flows with large scale vortices,densities can be measured, but pressures and velocities cannotbe deduced with the assumption of constant pressure gradient inthe normal direction The sensitivity of the mterferograms wasgood at a Mach number of 0 4 and a Reynolds number of 4 x 10to the 6th power/ft, the sensitivity worsened at smaller Machnumbers and Reynolds numbers, and improved at larger ones

Author

N83-27895# Department of Energy, Bartlesville, Okla EnergyTechnology CenterTHERMODYNAMICS OF ORGANIC COMPOUNDS Final Report,1 Oct. 1981-30 Sep. 1982B E GAMMON and N K SMITH Nov 1982 21 p refs(Contract AF-AFOSR-ISSA-82-00012, AF PROJ 2308)(AD-A125022, AFOSR-83-0047TR) Avail NTIS HC A02/MFA01 CSCL 21E

This research program consisted of an integrated andinterrelated effort of basic and applied research in chemicalthermodynamics and thermochemistry Knowledge of variation ofphysical and thermodynamic properties with molecular structurewas used to select compounds for study that because of highring strain or unusual steric effects may have good energycharacteristics per unit volume or per unit mass and thus be usefulin the synthesis of high energy fuels These materials weresynthesized, and their thermodynamic properties were evaluatedIn cooperation with researcher at Wright-Patterson Air Force Base,ramjet fuels currently in use were subjected to carefulthermodynamic evaluation by measurements of heat capacity,enthalpy of combustion and vapor pressure During the last yearof this effort, seven kerosene-type fuels produced by BritishPetroleum and seven jet fuels produced from shale oil werestudied Author (GRA)

483

17 SOCIAL SCIENCES

17

SOCIAL SCIENCES

Includes social sciences (general), administration and management,documentation and information science, economics and costanalysis, law and political science, and urban technology andtransportation

A83-34475AIRLINE SAFETY AND LABOR RELATIONS LAW - BALANCINGRIGHTS AND RESPONSIBILITYG D SKONING (Seyfarth, Shaw, Fairweather and Geraldson,Chicago, IL) (Flight Safety Foundation, Annual International AirSafety Seminar, 35th, Johannesburg, Republic of South Africa,Sept 6-9, 1982) Air Law (ISSN 0165-2079), vol 8, no 2, 1983, p104-116 refs

The legal status of conflicts between an airline's obligation toprovide the highest degree of safety and federal antidiscriminationstatutes is reviewed, with a focus on theage-60-mandatory-retirement and maximum-age-at-hiring policiesfor pilots, and on mandatory pregnancy leaves andphysical-handicap restrictions for flight attendants It is shown thatthe FAA highest-safety requirement has been broadly interpretedby the courts as a justification for policies which are prima facieviolations of the Age Discrimination in Employment Act or of TitleVII of the Civil Rights Act Safety-based criteria have generallybeen accepted as bona fide occupation qualifications under thoseacts Employees were found to be unjustifiably discriminatedagainst, however, when the airline could not show that a policywas safety-related, or when there was evidence suggesting thatsafety was being used as a pretext for economically determinedactions T K

A83-34851CANADIAN SYMPOSIUM ON AIR CUSHION TECHNOLOGY,16TH, CHARLOTTETOWN, PRINCE EDWARD ISLAND,CANADA, OCTOBER 19-21, 1982, PREPRINTSSymposium sponsored by the Canadian Aeronautics and SpaceInstitute and Hovercraft Society Ottawa, Canadian Aeronauticsand Space Institute, 1982, 110 p

Among the topics discussed are the application of systemidentification flight analysis techniques to the pitch-heave dynamicsof an air cushion vehicle (ACV), the dynamic stability of ACVs,surface impulse propulsion principles, the improvement of ACVperformance with wave-forming keels, an innovative icebreakervessel design for arctic environments, diesel versus gas turbineengine concepts in hovercraft design, combat damageconsiderations for ACVs, the potential application of militaryhovercraft in NATO's northern flank, and the U S Coast Guard'soperational evaluation of a 110-foot surface-effect ship Alsoconsidered are the design, development and testing of such ACVsas the AEROBAC AB-7, LARUS, VP-1, the HM5 prototype, andthe AP 1-88 OC

A83-34852APPLICATION OF SYSTEM IDENTIFICATION FLIGHTANALYSIS TECHNIQUES TO THE PITCH-HEAVE DYNAMICSOF AN AIR CUSHION VEHICLEP A SULLIVAN, P V HARTMANN, and T A GRAHAM (Toronto,University, Toronto, Canada) IN Canadian Symposium on AirCushion Technology, 16th, Charlottetown, Prince Edward Island,Canada, October 19-21, 1982, Preprints Ottawa, CanadianAeronautics and Space Institute, 1982, p 2-16 Research supportedby the National Research Council of Canada and Transport Canada,Natural Sciences and Engineering Research Council of Canadarefs(Contract NSERC-A-3378, NSERC-A-1613)

Flight test data obtained for the Vampire 1 Air Cushion Vehicleare analyzed The skirt used in these tests was of theuncompartmented segmented skirt type, and the test data,

consisting of the outputs from accelerometers, angular rate gyros,etc, was obtained by flying the vehicle over a ramp installed in a43-m diameter circular track The analysis employed a maximumlikelihood, Gauss-Newton system identification techniquedeveloped for the interpretation of aircraft flight test dataReasonable agreement was obtained beween the estimates ofstiffness and damping in pitch, and the corresponding valuesmeasured in the static pitch tests It was also confirmed that thehysteresis observed in the static pitch tests can have a majoreffect of vehicle dynamics O C

A83-34853AN OVER-VIEW OF UTIAS RESEARCH ON THE DYNAMICSTABILITY OF AIR CUSHION VEHICLESM J HINCHEY (Toronto, University, Toronto, Canada) INCanadian Symposium on Air Cushion Technology, 16th,Charlottetown, Prince Edward Island, Canada, October 19-21,1982,Preprints Ottawa, Canadian Aeronautics and Space Institute, 1982,p 17-29 Research supported by the National Research Councilof Canada and Transport Canada refs

Dynamic instabilities have been encountered by a number ofCanadian operators of air cushion vehicles This paper presentsan overview of research at the University of Toronto, Institute forAerospace Studies (UTIAS), dedicated to understanding thephenomenon It includes a brief review of theoretical andexperimental work on the destabilizing effect of cushion air supplyducts The duct-plenum system is shown to behave as a Helmholtzresonator with the slug of air in the duct oscillating on the plenumair spring For this work, a unique facility was developed whichused a large hollow sphere as a pneumatic filter to isolate theduct-plenum system from the fan The paper also outlines recentlycompleted work on limit cycle oscillations, skirt material damping,large air cushion platforms, and air cushions hovering over water

Author

A83-34855HOW TO IMPROVE AIR CUSHION VEHICLE PERFORMANCEWITH VUMP EQUIPPED WAVE-FORMING KEELSA JONES, JR (FASTCO, Virginia Beach, VA) IN CanadianSymposium on Air Cushion Technology, 16th, Charlottetown, PrinceEdward Island, Canada, October 19-21, 1982, Preprints Ottawa,Canadian Aeronautics and Space Institute, 1982, p 39-41

Vent-pump, or 'VUMP'-equipped Wave Forming (W-F) keelsare suggested as a means of imparting hydrodynamic lift to aircushion lift The planning surfaces of the W-F keels are lubricatedby air pumped by the ventun-effect action of the VUMP Theconcept is similar to that of the Muller-Thomamuhl (1915) aircushion hydroplane, although instead of requiring a blower, it ispowered by the action of the forward motion of the air cushionvehicle on the VUMP O C

A83-34858TECHNICAL ASPECTS OF THE AEROBAC AB-7J BOUDREAULT (Bombardier, Ltd, Valcourt, Quebec, Canada),G HERROUIN (Dubigeon-Normandie, S A, Paris, France), and DGAWISH IN Canadian Symposium on Air Cushion Technology,16th, Charlottetown, Prince Edward Island, Canada, October 19-21,1982, Preprints Ottawa, Canadian Aeronautics and Space Institute,1982, p 55-60

The AEROBAC AB-7, an off-road vehicle concept combiningair cushion and conventional tracks, is the subject of a feasibilitystudy which has as its goal the formulation of an economicalmeans of transportation in the northern regions of Canada (wherelow population density and harsh terrain make the building of aconventional transportation system prohibitive) Attention is givento the design features and projected performance capabilities ofthe AEROBAC AB-7, which with a 7 metric ton payload has aweight of 21 metric tons, and is able to travel at a maximumspeed of 30 km/hr over terrain that would be impassable forconventional off-road vehicles O C

17 SOCIAL SCIENCES

A83-34859'LARUS' AND 'VP-1' TESTED IN WINTER 1982S KORPPOO (Oy Wartsila AB, Helsinki, Finland) IN CanadianSymposium on Air Cushion Technology, 16th, Charlottetown, PrinceEdward Island, Canada, October 19-21, 1982, Preprints Ottawa,Canadian Aeronautics and Space Institute, 1982, p 61-63

Two air-cushion vehicles, 'Larus' and 'VP-1', were tested inthe south-western archipelago of Finland The tests were carriedout in March 1982, when the sea was frozen and covered with50 mm of snow During the tests 'Larus' operated independentlyand also towed 'VP-1' Measurements were made of the speed,resistance and manoeuvrability of the two craft Author

A83-34860NEW CONCEPT IN HOVERCRAFT DESIGN DIESEL VERSUSGAS TURBINESD E EMMAS IN Canadian Symposium on Air CushionTechnology, 16th, Charlottetown, Prince Edward Island, Canada,October 19-21, 1982, Preprints Ottawa, Canadian Aeronauticsand Space Institute, 1982, p 64-68

The fuel cost increases experienced during the 1970s compelledcertain hovercraft designers to investigate the relative advantagesof the use of lightweight diesel engines rather than the previouslyfavored gas turbines, which had higher fuel consumption TheAP1-88 hovercraft presently considered has been tested with bothair-cooled and water-cooled diesel engines Although fuelconsumption reduction was the paramount consideration in thetest program undertaken, engine weight reduction was also sought,and resulted in the choice of turbocharged versions of both theair- and water-cooled engines O C

A83-34861ACV LIFT AIR SYSTEMS - MORE PUFF FOR LESS POWERH S FOWLER (National Research Council, Ottawa, Canada) INCanadian Symposium on Air Cushion Technology, 16th,Charlottetown, Prince Edward Island, Canada, October 19-21,1982,Preprints Ottawa, Canadian Aeronautics and Space Institute, 1982,p 70-74 refs

While Air Cushion Vehicle lift air supplies are often consideredas merely isolated fans by designers, an attempt is presently madeto take into account all aerodynamic factors involved in fan intakeand exhaust duct design It is noted that the frequently employedfan scroll exhaust duct is not necessarily the most efficientalternative, and other are proposed within the constraints presentedby vehicle design Emphasis is put on overall air system stabilityand efficiency O C

A83-34862AP.1-88 CRAFT 001 PROTOTYPE CLEARANCE TRIALSR L WHEELER (British Hovercraft Corp, Ltd, East Cowes, Isleof Wight, England) IN Canadian Symposium on Air CushionTechnology, 16th, Charlottetown, Prince Edward Island, Canada,October 19-21, 1982, Preprints Ottawa, Canadian Aeronauticsand Space Institute, 1982, p 75-80

The AP1-88 001 is the first prototype of an 80-passengerhovercraft design which, relative to the SR N6-type craft whichhave served in the cross-Solent (U K) route for which the AP 1-88is intended since 1965, represents an entirely new designincorporating such novel features as a welded aluminum hull andfour air-cooled diesel engines with twin ducted propulsors A majorfeature retained m the new design from the latest of thedevelopment versions of the SR N6 craft is the highly responsive,low pressure ratio skirt which permits reduced propulsion and liftpower levels relative to weight, thereby improving ride comfort

OC

A83-34864OPERATIONAL DEPLOYMENT OF THE AIR CUSHIONVEHICLER W HELM (Bell Aerospace Canada Textron, Grand Bend, Ontario,Canada) IN Canadian Symposium on Air Cushion Technology,16th, Charlottetown, Prince Edward Island, Canada, October 19-21,1982, Preprints Ottawa, Canadian Aeronautics and Space Institute,1982, p 87-92

An analysis of air cushion vehicle program objectives is thebasis for the formulation of fielding and support plans, with thetype or types of vehicles to be used determining the requirementsfor the base of operations, the type and quality of ground supportequipment, and the supply of spare parts and special tools Payloadtypes, either passenger or cargo, also influence requirements,especially with respect to the provisioning of mechanical handlingequipment Mission profiles and route stage lengths determinefuel requirements Each operational deployment task isaccomplished through some function that is in turn influenced bythe preceding task The failure to identify any given task, or tomake allowances for those which have been identified, will havea detrimental impact on the achievement of program objectives

OC

A83-35052FROM VOYAGEUR ON - THE EXPLOITATION OF ANOPPORTUNITY TO DEVELOP A CANADIAN AIR CUSHIONVEHICLE INDUSTRYR W HELM (Bell Aerospace Canada Textron, Grand Bend, Ontario,Canada) IN Canadian Symposium on Air Cushion Technology,15th, Toronto, Canada, September 29, 30, 1981, ProceedingsOttawa, Canadian Aeronautics and Space Institute, 1981, p62-71

Experiences of Canadian developers of air cushion vehicles(ACV) are surveyed Markets for ACVs were projected to includeapplications as active river-crossing ferries, off-road freight hauling,air-cushion on-road transports, and icebreaking, as well as landingcraft in military use The first Canadian hovercraft was completedin 1972 and subjected to trials on Lake Ontario Several modelsof this Voyageur ACV were built, with learning and redesignexperience in operations, including offshore discharge of containerships in a military role The Viking, a small ACV with one powermodule and two propellers, was designed as an SAP vessel, butencountered sea-keeping problems The U S Army ordered twoVoyageurs, each able to carry 30 tons, in 1975 Designimprovements have recently been incorporated in the LACV-30s,of which eight have been ordered as amphibious landing craft forthe U S Army Older Voyageurs are currently employed as trainingcraft in the Gulf of Mexico M S K

A83-35053A NEW CLASS ACV - TANKER-FREIGHTERR G LONGAKER IN Canadian Symposium on Air CushionTechnology, 15th, Toronto, Canada, September 29, 30, 1981,Proceedings Ottawa, Canadian Aeronautics and Space Institute,1981, p 74-87

A qualitative examination of the concept-to-delivery to the CoastGuard of a 70 ST air cushion hoverbarge is presented Theentire process consumed only 51 weeks, beginning with a decisionto proceed with hardware that was rugged and reliable and requireda common welding rig and diesel engine tools The project wasthe Demonstration Program Alaskan Air Cushion vehicle with aneight wheel, hydraulically powered, dual direction driving systemThe axles were built to steer, level, extend, retract, and displacehorizontally about a central mounting shaft, and the vehicle wasoutfitted with all-terrain tires Contract specifications allowed 36short tons of fuel as part of the 70 ton cargo capacity The vehiclewas intended to transport freight and people between ports andremote Alaskan villages in all weather conditions Operatingpersonnel were brought in at the early manufacture phase Testruns in 20-27 in of new snow were performed at 7-10 mph, anda winter test program in Alaska covered 2600 mi Details of theexperience gained in the hoverbarge development are provided,including a checklist to summarize monthly activities M S K

485

17 SOCIAL SCIENCES

A83-35054DYNAMIC MODELING OF AN AIR CUSHION VEHICLEA J AMATO (ORI, Inc , Ship Technology Div , Silver Spring, MD)and D D MORAN (David W Taylor Naval Ship Research andDevelopment Center, Bethesda, MD) IN Canadian Symposiumon Air Cushion Technology, 15th, Toronto, Canada, September29, 30, 1981, Proceedings Ottawa, Canadian Aeronautics andSpace Institute, 1981, p 89-98 refs

A time domain nonlinear analytic model infour-degrees-of-freedom of the dynamic motion response of anair cushion supported vehicle is presented Predicted craft responseto both declining oscillation tests and gully overpassage arepresented and compared with published experimental data

Author

A83-35055COMPUTER STUDIES OF ACV HEAVE DYNAMICSSTABILIZATIONJ R AMYOT (National Research Council, Ottawa, Canada) INCanadian Symposium on Air Cushion Technology, 15th, Toronto,Canada, September 29, 30, 1981, Proceedings Ottawa, CanadianAeronautics and Space Institute, 1981, p 100-112

A hybrid computer model of an air cushion vehicle (ACV)capable of heave instability was postulated based on experimentaldata from a heave test rig The model was developed to studyautomatic vent valve control in ACV heave dynamics stabilizationResults have shown that it is a potentially effective means ofstabilizing ACV's and improving their ride quality Furthermore, itprovides the designer with more flexibility in determining plenumvolume and bearing area Author

A83-35056DEVELOPMENTS IN AIR CUSHION VEHICLE SPRAYSUPPRESSIONR W DYKE (Aerojet Liquid Rocket Co, Panama City, FL) INCanadian Symposium on Air Cushion Technology, 15th, Toronto,Canada, September 29, 30, 1981, Proceedings Ottawa, CanadianAeronautics and Space Institute, 1981, p 113-142

The development of improved spray aprons for air cushionvehicles has been driven by the need to improve crew andpassenger vision, as well as to reduce ice accretion, salt corrosion,erosion, and water ingestion in the engine and machinery roomsThe spray is produced by the cushion pressure {up to 70 Ib/sq ft)and the skirt design Initial studies involving a weighted apronpermitted development of an empirical expression that numericallymodeled the performance of the suppressor The most importantdesign considerations included the need to vent the spray, avoidoverloading the skirt, and to ensure the security of the suppressorattachments Specific successful designs implemented on theVoyageur 004 and, in another configuration, on the Jeff A (a Navyseacraft) are described, noting that the suppressors wereintroduced with no increase in drag M S K

A83-35057A DESIGN SYNTHESIS MODEL FOR ACV/SES LIFT SYSTEMSJ A TREMILLS (Defence Research Establishment Atlantic,Dartmouth, Nova Scotia, Canada), E G U BAND (Band, Lavisand Associates, Inc, Severna Park, MD), and R ST LAURENT(Davis Engineering, Ltd, Canada) IN Canadian Symposium onAir Cushion Technology, 15th, Toronto, Canada, September 29,30, 1981, Proceedings Ottawa, Canadian Aeronautics and SpaceInstitute, 1981, p 144-180 refs

This paper describes a design synthesis model for Air CushionVehicle (ACV) and Surface Effect Ship (SES) lift systems for craftof 100 to 10,000 tons The details of the basic technology, andthe cushion and the fan system design procedures and algorithmsare described The resulting interactive computer program isextensively modular and flexible in operation The program, whichis designed for easy modification to include different algorithms orto increase the size of the data base, outputs details on thecushion, air ducting, fans, power transmission and engines

Author

A83-35058SKIRTS - TIME FOR A NEW LOOK?H S FOWLER (National Research Council, Ottawa, Canada) INCanadian Symposium on Air Cushion Technology, 15th, Toronto,Canada, September 29, 30, 1981, Proceedings Ottawa, CanadianAeronautics and Space Institute, 1981, p 181-186

The development of skirts for air cushion vehicles (ACV) istraced, with a focus on skirts for overland hovercraft Initialapplications for ACVs were all for sea-going missions, and mainlyinvolved production of a flexible skirt to reduce weight and increaseclearance in hover However, the marine skirt is not directlyapplicable to the terrain changes, conditions, and roughnessencountered in overland operations Lighter fabrics permit theflexibility and low inertia necessary to rapid responses to obstaclesAbrasion of the material takes on the significance that flutter fatiguehas on water Low speed motion defrays the abrasive damage tothe skirt, allowing a stiffer and heavier material to be used Thesegment needed for spray suppression on water can be dispensedwith on land, although synthetic 'dragon scales' are underdevelopment in order to protect the skirt's flat underside from theabrasion caused by movements over ground obstacles M S K

A83-35059THE TRANSPORTATION DEVELOPMENT CENTRECONTRIBUTION TO AIR CUSHION TECHNOLOGYJ E LAFRAMBOISE (Transport Canada, TransportationDevelopment Centre, Montreal, Canada) IN Canadian Symposiumon Air Cushion Technology, 15th, Toronto, Canada, September29, 30, 1981, Proceedings Ottawa, Canadian Aeronautics andSpace Institute, 1981, p 187-207 refs

Projects in which the Transport Development Center of Canadahas been testing, redesigning, and defining applications for aircushion vehicles (ACV) are summarized Specific studies haveconcentrated on using hovercraft for overland transportation,evaluating the potential for using ACVs in the Northwest Territories,testing the effectiveness of ACVs as ice breakers, and analyzingair cushion system dynamics Trials have been performed withvarious skirt systems and overland hovercraft trailers Attentionhas been given to using the overland hovercraft as transportvehicles in sparsely populated regions, where traffic virtually stopsduring the spring thaw and where no road systems exist Twomodes of ice breaking, one suitable for rivers and one for lakes,have been defined and are under development Finally, the stabilityof the air cushion on large ACVs is being examined M S K

A83-35062LACV-30 SUPPORTABILITYJ SARGENT (U S Army, Mobility Equipment Research andDevelopment Command, Fort Belvoir, VA) IN CanadianSymposium on Air Cushion Technology, 15th, Toronto, Canada,September 29, 30, 1981, Proceedings Ottawa, CanadianAeronautics and Space Institute, 1981, p 244-266

The steps necessary for bringing the U S Army LACV-30amphibious support vehicles to operational status are reviewed,together with the projected missions Containerized cargo handlingraised the expected loads to 22 5 tons, delivered to a securedbeach through the surf and blowing sand from ships moored 1 5miles offshore The first air cushion vehicle tested was the CanadianVoyageur, which was the prototype for the LACV-30 craft Eachcraft in the LACV-30 program required 15 crewmembers, includingthe maintenance and repair teams Assigning specific teams toone craft enhanced efficiency and enthusiasm Procedures weredefined for recycling defective parts to the manufacturer andproviding for technical assistance on an organizational maintenancelevel Details of the manual definition, spare parts packaging,handling, and storage, transportation provisions, and designing theberthing facilities for the LACV-30 craft are summarized M S K

486

19 GENERAL

N83-27921# Committee on Commerce, Science, andTransportation (U S Senate)NASA AUTHORIZATION FOR FISCAL YEAR 1984Washington GPO 1983 227 p Hearing before the Subcommon Sci, Technol and Space of the Comm on Com, Sci andTransportation, 98th Congr, 1st Sess, 8, 9, 15 Mar 1983(GPO-19-200) Avail Subcommittee on Science, Technologyand Space

Fiscal year 1984 authorization for NASA are developed inrecognition of the close relationship between civilian and defenseaeronautical and space activities Author

19

GENERAL

N83-26783# Air Force Wright Aeronautical Labs,Wright-Patterson AFB, OhioAIR FORCE TECHNICAL OBJECTIVE DOCUMENT FY 1984R L VERGA Dec 1982 31 p SupersedesAFWAL-TR-81-4134(AD-A123961, AFWAL-TR-82-4201, AFWAL-TR-81 -4134) AvailNTIS HC A03/MF A01 CSCL 05A

This technical objective Document was prepared by theMaterials Laboratory and describes the Materials TechnologyPlanning Objectives (TPOs) for meeting future Air Force operationalneeds The six TPOs encompass the full spectrum of materialscapabilities required for future aircraft, missile, space, and electronicsystems - Thermal Protection Materials, Aerospace StructuralMaterials, Aerospace Propulsion Materials, Fluid, Lubricant, andElastomeric Materials, Protective Coatings and Materials, andElectromagnetic Windows and Electronics Presented for each TPOis the general objective, specific goals, technical approaches, anda Laboratory focal point who can facilitate face-to-face discussionswith Laboratory engineers and scientists GRA

487

SUBJECT INDEX

AERONAUTICAL ENGINEERING / A Continuing Bibliography (Supplement 165) SEPTEMBER 1983

Typical Subject Index Listing

SUBJECT HEADING

ACOUSTIC MEASUREMENT— A new measurement method for separating airborne and

structureborne noise radiated by aircraft type panels(NASA TP-2079] p 73 N83-11838

TITLEREPORTNUMBER

PAGENUMBER

NASAACCESSION

NUMBER

The subject heading is a key to the subject contentof the document The title is used to provide adescription of the subject matter When the title isinsufficiently descriptive of the document content,the title extension is added, separated from the titleby three hyphens The (NASA or AIAA) accessionnumber and the page number are included in eachentry to assist the user in locating the abstract inthe abstract section If applicable, a report numberis also included as an aid in identifying thedocument Under any one subject heading, theaccession numbers are arranged in sequence withthe AIAA accession numbers appearing first

ACCELERATED LIFE TESTSCanadian forces tracker aircraft full-scale fatigue test

at the national aeronautical establishmentp 433 A83-33548

Statistical study of TBO and estimation of accelerationfactors of ASMT for aircraft turbo-engine — AcceleratedSimulated Mission Endurance Testing

p 448 A83-35858

Accelerated Mission Testing of the Ft 10 Engine[AIAA PAPER 83-1235] p 453 A83-36298

Accelerated simulated mission endurance test of aturboshaft engine for military attack helicopterapplication[AIAA PAPER 83-1359] p 455 A83-36357

Development of simulated mission endurance testacceleration factors in determining engine componentserviceability and failure mode cnticality[AIAA PAPER 83-1409] p 457 A83-36398

ACCELERATION (PHYSICS)ACES M negative Gz restraint investigation

[AD-A124713] p 430 N83-25685

ACCELEBOMETERSModern technology and airborne engine vibration

monitoring systems[AIAA PAPER 83-1240] p 444 A83-36303

Statistical review of counting accelerometer data forNavy and Marine fleet aircraft[AD-A124966J p 443 N83 26834

ACCIDENT INVESTIGATIONForeign Technology Alert Bibliography Transportation

safety[PB83-101659] p430 N83-25686

ACCIDENT PREVENTIONForeign Technology Alert Bibliography Transportation

safety[PB83-101659] p 430 N83-25686

ACCURACYComputation of incompressible potential flow over an

airfoil using a high order aerodynamic panel method basedon circular arc panels[AD-A124B96] p 428 N83-26825

ACOUSTIC DUCTSFriction drag measurements of acoustic surfaces

[AIAA PAPER 83-1356] p 422 A83-36414ACOUSTIC MEASUREMENT

Full-scale measurements of blade-vortex interactionnoise p 482 A83-33505

ACOUSTIC PROPERTIESThe relationship between the aerodynamic and acoustic

characteristics of coaxial lets p 482 A83-35712A compact inflow control device for simulating flight fan

noise[NASATM-83349] p 482 N83-26643

ACTIVE CONTROLAircraft active controls New era in design

p 461 A83-35773ADAPTIVE CONTROL

Using adaptive control to synthesize invariant andpartially autonomous automatic stabilization systems

p460 A83-33900Aircraft active controls New era in design

p 461 A83-35773ADDITIVES

The effect of products based on higher fatty acids onthe performance characteristics of |et fuels

p 468 A83-34500An investigation of the effectiveness of smoke

suppressant fuel additives for turbojet applications[ADA125025] p 471 N83-27034

ADHESIVE BONDINGSome applications of ultrasonic methods for the quality

control of nonmetallic objects p 475 A83-36794Ultrasonic weld bonding of helicopter primary

structures[AD-A124645] p 477 N83-26081

ADIABATIC CONDITIONSTemperature response of a model to set-point changes

and conditioning in ETW p 465 N83-25721AERIAL PHOTOGRAPHY

Precision navigational filmstnps for use in DOD aircraft[AD-A124761] p 432 N83-25688

AERIAL RECONNAISSANCECanadian forces tracker aircraft full-scale fatigue test


AEROACOUSTICSThe aerodynamics of hyposonic velocities {On flows with

low Mach numbers) p417 A83-35535Edge tones in high-speed flows and their application

to multiple-jet mixing p 482 A83-36077Derivation of the fundamental equation of sound

generated by moving aerodynamic surfacesp 482 A83-36096

Mathematical models of the acoustic properties ofpropellers p 458 A83-36792

AERODYNAMIC CHARACTERISTICSCoupled flap-lag-torsional dynamics of hingeless rotor

blades in forward flight p 433 A83-33506ACV lift air systems - More puff for less power

p 485 A83-34861Calculation of subsonic flow past rectangular wings and

their combinations on the basis of a discrete vortexscheme p 418 A83-35541

The relationship between the aerodynamic and acousticcharactenstics of coaxial lets p 482 A83-35712

Aerodynamic optimization theory of A 3-D axial-flowrotor-bladmg via optimal control p 418 A83-35839

Numerical calculation of nonlinear aerodynamics ofwing-body configurations p 420 A83-36076

The aerodynamic design and performance of theGeneral Electric/NASA EEE fan — Energy EfficientEngine[AIAA PAPER 83-1160] p 451 A83-36252

STOL wind tunnel test results for a tacticalsupercruiser(AIAA PAPER 83-1224] p 420 A83-36291

Application ol 3D aerodynamic/combustion model tocombustor primary zone study[AIAA PAPER 83-1265] p 454 A83-36316

Aerodynamic measurements about a rotating propeller jwith a laser velocimeter[AIAA PAPER 83-1354] p 421 A83-36355 I

The motion dynamics of parachute systems — Russianbook p 422 A83-36450

AFTI/F-111 mission adaptive wing technologydemonstration program[AIAA PAPER 83-1057] p 438 A83-36468 I

Wind tunnel tests of over-the wing nacelles — supportedon'Stub-wings' p 422 A83-36916

Correction to the wing source velocity error inWoodward's USSAERO code p 423 A83-36920 I

Effect of empennage location on twin-engineafterbody nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2 - wind tunnel tests[NASA-TP-2116] p424 N83-25666

Analysis of nonplanar wing tip-mounted lifting surfaceson low-speed airplanes[NASA-CR-3684] p 424 N83-25667

A wind tunnel study of the effects of a close-coupledcanard on the aerodynamic characteristics of aforward-swept wing in incompressible flow[AD-A124722] p 425 N83-25673

F-14 rotary balance tests for an angle-of-attack rangeof 0 deg to 90 deg[AD-A124468] p 441 N83-25700

Proposed MIL standard and handbook Flying qualitiesof air vehicles Volume 2 Proposed MIL handbook[AD-A123726] p 441 N83-25704

Aircraft aerodynamic prediction method for V/STOLtransition including flow separation[NASA-CR-166467] p 426 N83-26818

AERODYNAMIC COEFFICIENTSMaterials and modelling technology for cryogenic

environment p 465 N83 25723AERODYNAMIC CONFIGURATIONS

Aerodynamic design of propfan powered transports[AIAA PAPER 83-1213] p 437 A83 36285

Selected advanced aerodynamics and active controlstechnology concepts development on a derivative B-747aircraft[NASA-CR-3295] p 442 N83-26831

AERODYNAMIC DRAGA technique to determine lift and drag polars in flight

p 422 A83-36913AERODYNAMIC INTERFERENCE

Wind tunnel tests of over the-wmg nacelles — supportedon 'stub-wings p 422 A83-36916

Experimental study of main rotor/tail rotor/airframeinteractions in hover Volume 1 Text and figures[NASA-CR-166485] p 427 N83 26820

AERODYNAMIC LOADSMaximum loading capability of axial flow compressors

[AIAA PAPER 83-1163] p 451 A83-36254Technical evaluation report on the Fluid Dynamics Panel

Specialists' Meeting on Prediction of Aerodynamic Loadson Rotorcraft[AGARD-AR-189] p 426 N83-25682

Static aeroelastic analysis of flexible wings viaNASTRAN, part 1[AD-A124662] p 477 N83-26099

Aerodynamic research on Tipvane wmdturbines[PB83-147413] p 479 N83-27476

AERODYNAMIC NOISEDerivation of the fundamental equation of sound


In flight acoustic test results for the SR-2 and SR-3advanced-design propellers[AIAA PAPER 83-1214] p 452 A83-36286

Low flight speed acoustic results for a supersonic inletwith auxiliary inlet doors[NASATM-83411) p 482 N83-27794

AERODYNAMIC STABILITYCorrelation and evaluation of mplane stability

characteristics for an advanced beanngless mam rotor[NASA-CR-166448] p 440 N83-25695

A-1

AERODYNAMIC STALLING SUBJECT INDEX

AERODYNAMIC STALLINGMaximum loading capability of axial flow compressors

[AIAA PAPER 83-1163] p 451 A83-36254Configuration development of a research aircraft with

post-stall maneuverability p 439 A83-36915The use of vortex generators as inexpensive compressor

casing treatment p 459 N83-26798Experimental studies of the separating confluent

boundary-layer Volume 1 Summary(NASA-CR-3655] p 427 N83-26822

Aircraft accident report IBEX Corporation Gates Leariet23, N100TA, Atlanta, near Savannah, Georgia, 6 May1982IPB83-910401] p430 N83-26827

Pilot human factors in stall/spin accidents of supersonicfighter aircraft(NASA-TM-84348] p 462 N83-26846

AERODYNAMICSThe aerodynamics of hyposonic velocities (On flows with

low Mach numbers) p417 A83-35535Feasibility study of three-dimensional holographic

interferometry for aerodynamics[NASA-CR-166483] p 483 N83-27845

AEROELASTICITYCoupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 433 A83-33506Nonlinear supersonic flutter of panels considering shear

deformation and rotary inertia p 473 A83-34315Integro-differential equations of the dynamics of elastic

systems in nonstationary flows — flight vehicle dynamicsin turbulent nonseparated flow p 474 A83-35933

Coupled flap-lag-torsional dynamics of hmgeless rotorblades in forward flight p 435 A83-35948

Flutter prediction in forward-swept wings by assumedmodes and strip theory[AD-A124715J p 461 N83-25719


AEROMANEUVERINGA small parameter method in problems of maneuvering

space vehicles with aerodynamic efficiencyp 467 A83-34849

AERONAUTICAL ENGINEERINGBring cohesion to handling-qualities engineering

p 434 A83-35772Aviation Executive Conference

(AD-A124581] p 416 N83-25654Some historical trends in the research and development

of aircraft1NASA-TM-84665] p417 N83-26785

AEROSOLSThe distribution of the disperse fraction of a polydisperse

let injected into a gas flow p 473 A83-34472AEROSPACE ENGINEERING

AGARD Bulletin Meetings, publications, membership[AGARD-BUL-83/1] p417 N83-26786

AEROSPACE TECHNOLOGY TRANSFERTechnology and engine demonstrator programs

[AIAA PAPER 83-1064) p 457 A83-36464AEROSPACE VEHICLES

Aerospace technology demonstrators/research andoperational options(AIAA PAPER 83-1054] p 438 A83-36465

AEROTHERMODYNAMICSTransient heat-transfer measurement technique in wind

tunnel and data analysis technique using systemidentification theory[AD-A124663] p 424 N83-25669

AFTERBODIESVectored thrust afterbody nozzles for future combat

aircraft p 448 A83-35859Empennage/afterbody integration for single and

twin-engine fighter aircraft[AIAA PAPER 83-1126] p 420 A83-36235

Effect of empennage location on twin-engineafterbody-nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2 — wind tunnel tests[NASA-TP-2116] p424 N83-25666

AIR BREATHING ENGINESInternational Symposium on Air Breathing Engines, 6th,

Pans, France, June 6-10, 1983, Symposium Papersp 445 A83-35801

NASA propulsion controls research[NASA-TM-83343] p 458 N83-25711

AIR DROP OPERATIONSWind tunnel investigation of cargo extraction parachutes

in the wake of a Lockheed C-141B Starlifter aircraft[AD-A124523] p 425 N83-25675

AIR FLOWWind tunnel investigation of cargo extraction parachutes


An experimental/analytical investigation into theperformance of a 20-percent thick, 8 5-percent cambered,circulation controlled airfoil[AD-A1247321 p 441 N83-25701

Generalization of the air-|et propulsion systems, the 'N'flow turbo-iet engine[AD-A123932] p 459 N83-25715

Design of choking cascade turns(AD-A124792J p 477 N83-26023

Injection, atomization, ignition and combustion of liquidfuels in high-speed air streams[AD-A125237] p 471 N83-27033

AIR INTAKESThe swirl in an S-duct of typical air intake proportions

p418 A83-35620Experimental study of strength and existence domain

of ground-to-air inlet vortices by ground board staticpressure measurements(PB83-144865] p 460 N83-26843

Low flight speed acoustic results for a supersonic inletwith auxiliary inlet doors[NASA-TM-83411] p 482 N83-27794

AIR JETSEffect of air, liquid and injector geometry variables upon

the performance of a plain-jet airblast atomizerp473 A83-35809

Edge tones in high-speed flows and their applicationto multiple-iet mixing p 482 A83-36077

AIR LAUNCHINGDesign of choking cascade turns

[AD-A124792] p 477 N83-26023AIR LAW

Airline safety and labor relations law - Balancing rightsand responsibility p 484 A83-34475

AIR NAVIGATIONAdvanced navigation systems and fuel conservation

p428 A83-33545A theoretical framework for analysis of lateral position

errors in VOR let-route systems p 431 A83-35273Omega application in the Indonesian region

p 431 A83-35599Performance capabilities of photographic flight

navigation and sensor orientation systemsp431 A83-36122

AIR POLLUTIONThe effects of fuel properties upon pollutants present

in gas turbine aero-engines p 469 A83-35813Effect of sand erosion on the performance deterioration

of a single stage axial flow compressorp 448 A83-35854

A JT8D low emissions combustor by radial zoning[AIAA PAPER 83-1324] p 455 A83-36339

An investigation of the effectiveness of smokesuppressant fuel additives for turbojet applications[AD-A125025] p 471 N83-27034

AIR TO AIR REFUELINGDynamic characteristics of aenal refueling systems

(AD-A124770) p 442 N83-26830Lateral flying qualities of highly augmented fighter

aircraft, volume 1[AD-A118070] p443 N83-26835

AIR TRAFFICFAA aviation forecasts Fiscal years 1983-1994

[AD-A124611] p416 N83-25652AIR TRAFFIC CONTROL

Advanced navigation systems and fuel conservationp428 A83-33545

On the use of height rules in off-route airspacep 431 A83-35274

Computer model of a collision-avoidance system for airtraffic control p 431 A83-35275

All weather heliports and airway system - The futureneed p 463 A83-36073

The man-vehicle systems research facility - A new NASAaeronautical R & D facility[AIAA PAPER 83-1098] p 463 A83-36218

Aviation Executive Conference[AD-A124581] p 416 N83-25654

A strategy is needed to deal with peaking problems atinternational airports[GAO/GGD-83 4] p 429 N83-25683

FAA's plan to improve the air traffic control system Astep in the right direction but improvements and bettercoordination are needed[GAO/AFMD-83-34] p 432 N83-25687

Numerical treatment of Doppler radar signals — airportradar, video data[ENST-E-82014] p 478 N83-27114

AIR TRANSPORTATIONConcepts for a future joint airlift development program

[AIAA PAPER 83-1591] p 429 A83-36951USAF mobility requirements — USER

REQUIREMENTS[AIAA PAPER 83-1588] p 429 A83-36954

AIRBORNE EQUIPMENTLaser safety of air bathymetry

[FOA-C-30292-E1] p 478 N83-27210AIRBORNE/SPACEBORNE COMPUTERS

Some aspects of development of power plant optimumcontrol to increase aircraft fuel efficiency

P447 A83-35841Flight management concepts development for fuel

conservation p 447 A83-35843Compensation for time delay in flight simulator

visual-display systems[AIAA PAPER 83-1080] p 464 A83-36222

F/A-18A Inflight Engine Condition Monitoring System(IECMS)[AIAA PAPER 83-1237] p 453 A83-36300

AIRCRAFT ACCIDENTSAircraft accident report IBEX Corporation Gates Leariet

23, N100TA, Atlanta, near Savannah, Georgia, 6 May1982[PB83-910401 ] p 430 N83-26827

AIRCRAFT CARRIERSSimulator design features for carrier landing Part 2

In-simulator transfer of training[AD-A124024] p 466 N83-25733

AIRCRAFT CONFIGURATIONSThe response of aircraft to pulse excitation

p434 A83-34312KC-135/CFM56 re-engine The best solution

[AIAA PAPER 83-1374] p 456 A83-36367The F-16 - A technology demonstrator, a prototype, and

a flight demonstrator[AIAA PAPER 83-1063] p 438 A83-36467

Configuration development of a research aircraft withpost-stall maneuverability p 439 A83-36915

Wind tunnel tests of over-the-wing nacelles — supportedon 'stub-wings' p 422 A83-36916

Effect of empennage location on twin-engineafterbody-nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2 — wind tunnel tests[NASA-TP-2116] p424 N83-25666

Experimental studies of the separating confluentboundary-layer Volume 1 Summary[NASA-CR-3655] p 427 N83-26822


AIRCRAFT CONSTRUCTION MATERIALSTechnology status for an advanced supersonic

transport[SAE PAPER 820955] p 433 A83-33627

Highly stressed materials, with aviation considered asan example — Book p 467 A83-33951

Materials in the mirror of aviation criteriap 434 A83-33952

Matenal, structural component, service life — of aircraftconstruction materials p 468 A83-33953

Structural members made of high-strength castaluminum and their properties — and reduction of aircraftproduction costs p 468 A83-33954

High-strength aluminum high-quality casting alloy inaeronautics and astronautics p 468 A83-33955

Light aircraft and sailplane structures in reinforcedplastics p 435 A83-36065

XB-70 technology advancements[AIAA PAPER 83-1048] p 437 A83-36460

Air Force technical obiective document FY 1984[AD-A123961] p 487 N83-26783

AIRCRAFT CONTROLAdvanced navigation systems and fuel conservation

p428 A83-33545Bring cohesion to handling-qualities engineering

p 434 A83-35772Aircraft active controls - New era in design

p 461 A83-35773Use of flight test results to improve the flying qualities

simulation of the B-52H weapon system trainer(AIAA PAPER 83-1091] p 437 A83-36215

Definition of vectored nonaxisymmetric nozzle plumes— for aircraft thrust vector control[AIAA PAPER 83-1290] p 423 A83-36924


Lateral flying qualities of highly augmented fighteraircraft, volume 1[AD-A118070] p443 N83-26835

Determination of stability and control parameters of ageneral aviation airplane from flight data[NASA-TM-84635] p 461 N83-26844

AIRCRAFT DESIGNThe Dash 8 development program

p433 A83-33546A complete introduction to the revolutionary new way

to fly ultralights — Book p415 A83-33622

A-2

SUBJECT INDEX AIRCRAFT INDUSTRY

Technology status for an advanced supersonictransport[SAE PAPER 820955] p 433 A83-33627

Applications of advanced upper surface blowingpropulsive-lift technology[SAE PAPER 820956J p 433 A83 33628

Prop-fan powered aircraft - An overview[SAE PAPER 820957] p 434 A83-33629

Materials in the mirror of aviation criteriap 434 A83-33952

Recent studies at NASA-Langley of vortical flowsinteracting with neighboring surfaces

p417 A83-33972SAAB-Fairchild 340 - Transatlantic frontrunner

p 434 A83-35623Aircraft design philosophy I - Lee Begin of Northrop


p 461 A83-35773Design and development of a small gasturbme engine

Results today - A basis for design criteria of a nextgeneration p 446 A83-35829

Inlet, engine, airframe controls integration developmentfor supercruismg aircraft p 447 A83-35842

Light aircraft and sailplane structures in reinforcedplastics p 435 A83-36065

The history of V/STOL aircraft p 435 A83-36074Progress in propulsion system/airframe structural

integration[AIAA PAPER 83-1123] p 437 A83-36234

Aerodynamic design of propfan powered transports[AIAA PAPER 83-1213] p 437 A83-36285

Aircraft Prototype and Technology DemonstratorSymposium, Dayton, OH, March 23, 24, 1983,Proceedings p415 A83-36457

Prototypmg for fun and profit — military aircraft design[AIAA PAPER 83 1045] p 415 A83-36458

From new technology development to operationalusefulness B-36, B-58, F-111/FB-111[AIA PAPER 83-1046] p415 A83-36459


Variable sweep wing design[AIAA PAPER 83 1051] p 438 A83-36461

The application of low-cost demonstrators foradvancead fighter technology evaluation[AIAA PAPER 83-1052] p 438 A83-36462

YAV-8B flight demonstration program[AIAA PAPER 83-1055] p 438 A83-36466

The F-16 - A technology demonstrator, a prototype, anda flight demonstrator(AIAA PAPER 83-1063] p 438 A83-36467

AFTI/F-111 mission adaptive wing technologydemonstration program[AIAA PAPER 83 1057] p 438 A83-36468

Design for testing of a low altitude night-in-weatherattack system[AIAA PAPER 83-1061] p 432 A83-36470

The Northrop Flying Wing prototypes[AIAA PAPER 83-1047] p 416 A83-36471

Large jet aircraft validation and demonstrations - Anoverview of Boeing experience[AIAA PAPER 83-1049] p 439 A83-36472

The F-5 story - Prototype and technologydemonstrator[AIAA PAPER 83-1062] p 439 A83-36473

AFTI/F-16 technology demonstrator[AIAA PAPER 83-1059] p 439 A83-36474

Generalized maximum specific range performancep 439 A83-36918

The future of the manned aircraft p 416 A83-36960Some historical trends in the research and development

of aircraft[NASA-TM-846651 p417 N83-26785

Statistical experimental designs in computer aidedoptimal aircraft design p 442 N83-26812

Status, trends and implications of carbon fiber materialuse[PB83-147751] p 471 N83-26934

AIRCRAFT ENGINESThe influence of defects on the operational strength

of disks and wheels in engines p 472 A83-33964Thermal cycling in compact plate-fm heat exchangers

— in aircraft gas turbines p 445 A83 34253AR 318 - Italy's low-cost GA turboprop

p 445 A83-35675International Symposium on Air Breathing Engines, 6th,

Pans, France, June 6-10, 1983, Symposium Papersp 445 A83-35801

The effects of fuel properties upon pollutants presentin gas turbine aero-engines p 469 A83-35813

The prediction of performance of turbojet engine withdistorted inlet flow and its experimental studies

p446 A83-35832Cost effective performance restoration of high by-pass

engines p 447 A83-35833

Numerical computation of turbulent flow around thespinner of a turbofan engine p 418 A83-35838


p 447 A83-35841The transient performance of turboiet engines and axial

compressors p 447 A83-35847Development of a turboiet engine simulator for scale

model wind tunnel testing of multi-mission aircraftp 447 A83-35848

Propulsion system simulation technique for scaled windtunnel model testing p 463 A83-35850

Experimental study of a high-through-flow transonic axialcompressor stage p419 A83-35853

Effect of sand erosion on the performance deteriorationof a single stage axial flow compressor

p 448 A83-35854Effect of humidity on jet engine axial-flow compressor

performance p 448 A83-35856Statistical study of TBO and estimation of acceleration

factors of ASMT for aircraft turbo-engine — AcceleratedSimulated Mission Endurance Testing

p 448 A83-35858Ground simulation of engine operation at altitude

p 463 A83-35863The effect of variation of diffuser design on the

performance of centrifugal compressorsp 448 A83-35866

Component life reduction due to use of AVGAS in gasturbine engines p 449 A83-35869

Life estimation methods of gas turbine rotatingcomponents p 449 A83-35870

Containment of turbine engine fan bladesp 449 A83-35871

Investigation methods on residual stresses in aeroengines components p 449 A83-35879

Stress analysis of critical areas of low-pressurecompressor-disc assembly of a developmentalaero-engine p 449 A83-35880

Simulator fidelity and flight test data - Improving the flightperformance of the B-52H WST production unit flightstation simulator[AIAA PAPER 83-1075] p 436 A83-36204

Progress in propulsion system/airframe structuralintegration[AIAA PAPER 83-1123] p 437 A83-36234

Simulation of advanced engine lubrication and rotordynamics systems - Rig design and fabrication[ AIAA PAPER 83-t 133 ] p 450 A83-36238

The performance of single-shaft gas turbine loadcompressor auxiliary power units[AIAA PAPER 83-1159] p 451 A83-36251

A survey of trends in modern turbine technology[AIAA PAPER 83-1174] p 451 A83-36260

Advanced turboprop and dual cycle engine performancebenefits and installation options on a Mach 0 7 shorthaultransport aircraft[AIAA PAPER 83-1212] p 452 A83-36284

A Monte Carlo simulation of the engine developmentprocess[AIAA PAPER 83-1230] p 452 A83-36294

Nondestructive evaluation methods for implementationof damage-tolerant designed gas turbine enginecomponents[AIAA PAPER 83-1232] p 452 A83-36295

Aircraft engine inlet pressure distortion testing in aground test facility[AIAA PAPER 83-1233] p 453 A83-36296

Deterioration trending enhances |et engine hardwaredurability assessment and part management[AIAA PAPER 83-1234] p 453 A83-36297

Accelerated Mission Testing of the F110 Engine[AIAA PAPER 83-1235] p 453 A83-36298

Integrated propulsion-aircraft control evaluation for acurrent Navy fighter[AIAA PAPER 83-1236] p 453 A83-36299


Flight/propulsion control system integration[AIAA PAPER 83-1238] p 453 A83-36301

United Kingdom military engine usage, condition andmaintenance systems experience[AIAA PAPER 83-1239] p 453 A83-36302

Modern technology and airborne engine vibrationmonitoring systems[AIAA PAPER 83-1240] p 444 A83-36303

Comparison of an expenence with full authority digitalengine controls in rotary wing and let-lift VSTOL aircraft[AIAA PAPER 83-1241 ] p 454 A83-36304

Results of tests of a rectangular vectoring/reversingnozzle on an F100 engine[AIAA PAPER 83-1285] p 454 A83-36322

Advanced techniques for gas and metal temperaturemeasurements in gas turbine engines[AIAA PAPER 83-1291] p 444 A83-36325

Application of thin film strain gages and thermocouplesfor measurement on aircraft engine parts[AIAA PAPER 83-1292] p 444 A83-36326

Development trends in engine durability -- for USAFaircraft gas turbines[AIAA PAPER 83-1297] p 455 A83-36329

Development and application of a liquid-cooled V-8piston engine for general aviation aircraft[AIAA PAPER 83-1342] p 455 A83-36347

Performance capability of a Compact MultimissionAircraft Propulsion Simulator[AIAA PAPER 83-1358] p 464 A83-36356

KC-135/CFM56 re-engine - The best solution[AIAA PAPER 83-1374] p 456 A83 36367

Introducing the Rolls-Royce Tay[AIAA PAPER 83-1377] p 456 A83 36368

The impact of engine usage on life cycle cost[AIAA PAPER 83-1406] p 456 A83 36395

LCC evaluation of advanced engine damage tolerancegoals for a hot-section disk — in aircraft engines[AIAA PAPER 83-1407] p 456 A83-36396

Configuration selection and technology transition in 5000SHP class engines[AIAA PAPER 83-1411] p 457 A83-36400

Fighter engine cycle selection[AIAA PAPER 83-1300] p 457 A83-36412

Friction drag measurements of acoustic surfaces[AIAA PAPER 83-1356] p 422 A83-36414

Propulsion prototypes at general electric[AIAA PAPER 83-1053] p 457 A83-36463

Technology and engine demonstrator programs[AIAA PAPER 83-1064] p 457 A83-36464


Advanced propulsion controls - A total system viewp457 A83-36612

Electrohydraultc fuel-flow regulator forgas-turbine-engine control systems p 458 A83-36793

V/STOL status from the engine technology viewpointp 458 A83-36912


An update on high output lightweight diesel engines foraircraft applications[AIAA PAPER 83-1339] p 458 A83-36925

Development and production cost estimatingrelationships for aircraft turbine engines[AD-A123753] p 459 N83-25714

Dynamic distortion in a short s-shaped subsonic diffuserwith flow separation — Lewis 8 by 6 foot Supersonic WindTunnel[NASA-TM-84312] p 459' N83-26838

Method of studying the operating temperature of gasturbines — aeroengines[PNR-90159] p460 N83-26842

AIRCRAFT EQUIPMENTFlight operations A study of flight deck management

— Book p428 A83-33767Aircraft equipment random vibration test criteria based

on vibrations induced by turbulent airflow across aircraftexternal surfaces[AD-A123281] p 440 N83-25696

AIRCRAFT FUEL SYSTEMSThermal stability of alternative aircraft fuels

[AIAA PAPER 83-1143] p 470 A83-36243Dynamic characteristics of aerial refueling systems

[AD-A124770] p 442 N83-26830AIRCRAFT FUELS

Further studies on the prediction of spray evaporationrates — for aircraft fuels p 468 A83-35811


Thermal stability of alternative aircraft fuels[AIAA PAPER 83-1143] p 470 A83-36243

AIRCRAFT GUIDANCEGuidance control systems for aircraft on airport

surfaces[AIAA PAPER 83-1579] p 429 A83-36953

AIRCRAFT HAZARDSA contribution to airworthiness certification of gas turbine

disks p449 A83-35872Aircraft lightning-induced voltage test technique

developments[ NASA CR-170403 ] p 442 N83-26829

RF radiation from lightning correlated with aircraftmeasurements during storm hazards-82[NASA-TM-85007] p 479 N83-27537

AIRCRAFT HYDRAULIC SYSTEMSDetermination of the sensitivity of U S Air Force aircraft

hydraulic system components to paniculatecontamination p 475 A83-36910

AIRCRAFT INDUSTRYMaterials in the mirror of aviation cntena

p 434 A83-33952

A-3

AIRCRAFT INSTRUMENTS SUBJECTINDEX

Aviation Executive Conference[AD-A124581] p 416 N83-25654

AIRCRAFT INSTRUMENTSPerformance capabilities of photographic flight

navigation and sensor orientation systemsp 431 A83-36122

Advanced display techniques for training themulti-member tactical air crew| AIAA PAPER 83 1079] p 443 A83-36207

GE's APG-67 - Fighter radar with a futurep 432 A83-36625

AIRCRAFT LANDINGLateral flying qualities of highly augmented fighter

aircraft volume 1IADA118070] p 443 N83-26835

A flight-test and simulation evaluation of the longitudinalfinal approach and landing performance of an automaticsystem for a light wing loading STOL aircraft[NASA-TM-84270] p 461 N83-26845

AIRCRAFT MAINTENANCECost effective performance restoration of high by-pass

engines p 447 A83-35833Statistical study of TBO and estimation of acceleration

factors of ASMT for aircraft turbo engine — AcceleratedSimulated Mission Endurance Testing

p 448 A83-35858Analysis of F-16 radar discrepancies

[AD-A124749J p 476 N83-25948AIRCRAFT MANEUVERS

Impact damping and airplane towingp 428 A83-33625

A high speed wind tunnel test evaluation of STOLdedicated advanced exhaust nozzle concepts[AIAA PAPER 83-1225] p 421 A83-36292

Dynamics of air combat p416 A83-36914AIRCRAFT MODELS


Wind tunnel investigation of cargo extraction parachutesin the wake of a Lockheed C-141B Starlifter aircraft[AD-A124523] p 425 N83-25675

AIRCRAFT NOISEFull-scale measurements of blade vortex interaction

noise p 482 A83-33505In-flight acoustic test results for the SR-2 and SR-3

advanced-design propellers[AIAA PAPER 83 1214] p 452 A83-36286


Aviation Executive Conference[AD-A124581] p416 N83-25654

FAA integrated noise model validation Analysis of aircarrier flyovers at Seattle Tacoma Airport[AD-A124097] p 479 N83-26320

AIRCRAFT PARTSNumerical simulation of electrothermal de-icing

systems[AIAA PAPER 83-0114] p 428 A83-36043

Some applications of ultrasonic methods for the qualitycontrol of nonmetallic objects p 475 A83-36794

In-flight computation of helicopter transmission fatiguelife expenditure p 439 A83-36921

AIRCRAFT PERFORMANCEPerformance flight testing — Book

p 433 A83-33621Aircraft design philosophy I - Lee Begin of Northrop

p434 A83-35624Preliminary investigation on the performance of

regenerative turbofan with inter-cooled compressor andits influence to aircraft p 446 A83-35830


Simulator fidelity and flight test data - Improving the flightperformance of the B 52H WST production unit flightstation simulator[AIAA PAPER 83-1075] p 436 A83-36204


Introducing the Rolls-Royce Tay[AIAA PAPER 83-1377] p 456 A83-36368


Variable sweep wing design[AIAA PAPER 83-1051] p 438 A83-36461


A technique to determine lift and drag polars in flightp 422 A83-36913



Experimental analysis of the performance of an annularperipheral jet vehicle in ground effect(AD-A124949] p 443 N83-26832

AIRCRAFT PILOTSTheory underlying the peripheral vision horizon device

[AD-A124426] p 445 N83-25710AIRCRAFT PRODUCTION

Lasers in aircraft construction — Russian bookp472 A83-34170

SAAB-Fairchild 340 - Transatlantic frontrunnerp434 A83-35623

Aircraft production technology (2nd revised and enlargededition) — Russian textbook p415 A83-36443

AIRCRAFT PRODUCTION COSTSStructural members made of high-strength cast

aluminum and their properties — and reduction of aircraftproduction costs p 468 A83-33954


A tubular braided composite mam rotor blade sparp435 A83-35949


AIRCRAFT RELIABILITYA contribution to airworthiness certification of gas turbine

disks p449 A83-35872Mathematical models of the acoustic properties of

propellers p 458 A83-36792Airworthiness and flight characteristics test Part 2

YAH-64 advanced attack helicopter[AD-A125270] p 442 N83-25705

AIRCRAFT SAFETYThe influence of defects on the operational strength

of disks and wheels in engines p 472 A83-33964Runway surface condition sensor specification guide

[AC-150/5220-13A] p 465 N83-25728AIRCRAFT SPECIFICATIONS

CF34 upgrades Challenger capabilitiesp434 A83-35315

AIRCRAFT SPINF-14 rotary balance tests for an angle-of-attack range

of 0 deg to 90 deg[AD-A124468] p 441 N83-25700

Pilot human factors in stall/spin accidents of supersonicfighter aircraft[NASA-TM-84348] p 462 N83-26846

AIRCRAFT STABILITYUsing adaptive control to synthesize invariant and

partially autonomous automatic stabilization systemsp 460 A83 33900

Application of maximum likelihood estimation to theidentification of the stability derivatives of a wide bodytransport aircraft p 460 A83-35121

In-flight simulation at the U S Air Force and Naval TestPilot Schools[AIAA PAPER 83-1078] p 436 A83-36206

Experimental testing of flying qualities theories[AD-A124699] p 440 N83-25697

Determination of stability and control parameters of ageneral aviation airplane from flight data[NASA-TM-84635] p 461 N83 26844

AIRCRAFT STRUCTURESMaterial, structural component, service life — of aircraft

construction materials p 468 A83-33953Structural members made of high-strength cast

aluminum and their properties — and reduction of aircraftproduction costs p 468 A83 33954

Light aircraft and sailplane structures in reinforcedplastics P 435 A83-36065

Advanced manufactunng development of a compositeempennage component for L-1011 aircraft[NASA-CR-172657] p 440 N83-25694

Aircraft equipment random vibration test criteria basedon vibrations induced by turbulent airflow across aircraftexternal surfaces[AD-A123281] p 440 N83-25696

Evaluation of low-cost aluminum composites for aircraftengine structural applications[NASA-TM-83357] p 470 N83-25790

A parametric study of surface imperfections and smallcutouts in a composite panel(AD-A124739] p 470 N83-25793

Composite material aircraft electromagnetic propertiesand design guidelines[AD-A124016] p 470 N83-25795

AIRCRAFT SURVIVABILITYSurvivability of interdiction aircraft Sensitivity to terrain

following, command altitude, velocity and electroniccounter measures[AD-A124870] p 443 N83-26833

AIRFIELD SURFACE MOVEMENTSGuidance control systems for aircraft on airport


AIRFOILSNumerical simulation of airfoil ice accretion

[AIAA PAPER 83-0112] p 428 A83-36042Prediction of stagnation flow heat transfer on

turbomachinery airfoils[AIAA PAPER 83-1173] p 420 A83-36259

Natural laminar flow data from full-scale flight andwind-tunnel experiments p 422 A83-36409

High Reynolds number tests of the CAST 10-2/DOA 2airfoil in the Langley 0 3-meter transonic cryogenic tunnel,phase 1[NASA-TM-84620] p 424 N83-25660

Application of a finite difference method to the transonicairfoil problem[AD-A124720] p 425 N83-25674

Finite differecnce catcultion of an mviscid transonic flowover oscillating airfoils[AD-A123982] p 426 N83-25677

Design and analysis of a subcritical airfoil for highaltitude, long endurance missions[AD-A124757] p 441 N83-25702

Resonance tests on the tail of a CT4 aircraft[AD-A124566] p 441 N83-25703

Gust response prediction of an airfoil using a modifiedvon Karman-Pohlhausen technique[AD-A124716] p 461 N83-25718

Model mount system for testing flutter[NASA-CASE-LAR-12950-1] p 465 N83-25727

The use of vortex generators as inexpensive compressorcasing treatment p 459 N83-26798

Experimental studies of the separating confluentboundary-layer Volume 1 Summary[NASA-CR-3655] p 427 N83-26822

Computation of incompressible potential flow over anairfoil using a high order aerodynamic panel method basedon circular arc panels[AD-A124896] p 428 N83-26825

Calculation of boundary layers near the stagnation pointof an oscillating airfoil[NASA-TM-84305] p 478 N83-27148

Implicit upwind methods for the compressibleNavier-Stokes equations[NASA-TM-84364] p 478 N83-27149

AIRFRAMESMicroeconomic models for process development

p 472 A83-33650On improving the fatigue performance of a double-shear

lap joint p 473 A83-34744Inlet, engine, airframe controls integration development

for supercruising aircraft p 447 A83-35842Aviation Executive Conference

[AD-A124581] p 416 N83-25654Airframe RDT&E cost estimating A justification for and

development of unique cost estimating relationshipsaccording to aircraft type[AD-A123848] p 417 N83-25656

Ultrasonic weld bonding of helicopter primarystructures[AD-A124645] p 477 N83-26081

AIRLINE OPERATIONSWorldwide aviation outlook — for passenger and freight

traffic 1982-1992(AIAA PAPER 83-1597] p 429 A83-36952

A strategy is needed to deal with peaking problems atinternational airports[GAO/GGD-83-4] p 429 N83-25683

AIRPORT LIGHTSU S sets own standards for airport lighting

p463 A83-35625AIRPORTS

FAA aviation forecasts Fiscal years 1983-1994[AD-A124611] p416 N83-25652


AICUZ (Air Installation Compatible Use Zone) report[AD-A124974] p 483 N83-27801

AIRSHIPS1983 LTA technology assessment

[AIAA PAPER 83-1617] p 437 A83-36406AIRSPACE


AIRSPEEDA true air speed sensor for miniature unmanned

aircraft p 444 A83 36613ALGORITHMS

An algorithm of flight simulation on a dynamic stand ofsupport type p 462 A83-34429

A modified algorithm for determining structuralcontrollability p 480 A83 36455

Numerical treatment of Doppler radar signals — airportradar video data[ENST-E-82014] p 478 N83-27114

A-4

SUBJECT INDEX BOUNDARY LAYER TRANSITION

Sandia Helicopter Acoustic Detector (SHAD)IDE82-018925] p 483 N83-27803

ALL-WEATHER AIR NAVIGATIONAll weather heliports and airway system - The future

need p 463 A83-36073ALTERNATIVES

Emergency fuels technology[AD-A125275] p 471 N83-25904

ALTITUDEPerformance capabilities of photographic flight

navigation and sensor orientation systemsp43t A83-36122

ALUMINUM ALLOYSStructural members made of high-strength cast



Evaluation of low-cost aluminum composites for aircraftengine structural applications1NASATM-83357] p 470 N83-25790

AMPLIFICATIONHigh gain error actuated flight control systems for

continuous linear multivanable plants[ AD A124871] p 462 N83-26848

ANGLE OF ATTACKHigh angle-of-attack cascade measurements and

analysis p419 A83-35875Seven-hole cone probes for high angle flow

measurement Theory and calibrationp 474 A83-36085

F-14 rotary balance tests for an angle-of-attack rangeof 0 deg to 90 deg[ADA124468] p 441 N83-25700


ANGULAR VELOCITYComputation of incompressible potential flow over an

airfoil using a high order aerodynamic panel method basedon circular arc panels[AD A124896J p 428 N83-26825

ANNULAR FLOWEffect of entry boundary layer thickness on secondary

flows in an annular cascade of turbine nozzle and rotorblades p419 A83-35868

ANNULAR NOZZLESModel aerodynamic test results for a refined actuated

inlet ejector nozzle at simulated takeoff and cruiseconditions[NASA-CR 168051] p 426 N83-26816

ANTENNA ARRAYSNew advances in wide band dual polarization antenna

elements for EW applications p 430 A83-35087ANTENNA DESIGN

New advances in wide band dual polarization antennaelements for EW applications p 430 A83-35087

A rapid-tuning high-power pod-mounted VHP antennasystem p 430 " A83-35088

Multimode planar spiral for OF applicationsp 430 A83-35089

A network formulation for phased arrays - Applicationto log-periodic arrays of monopoles on curved surfaces

p431 A83-35090Comparative analysis of a phase and an amplitude

processor for amplitude monopulse systemsp431 A83-35192

ANTENNA RADIATION PATTERNSMultimode planar spiral for DF applications

p 430 A83-35089Comparative analysts of a phase and an amplitude

processor for amplitude monopulse systemsp 431 A83-35192

ANTIMISTING FUELSFeasibility of a full-scale degrader for antimisting

kerosene[AIAA PAPER 83-H37) p 469 A83-36240

APPROACH CONTROLA flight test and simulation evaluation of the longitudinal

final approach and landing performance of an automaticsystem for a light wing loading STOL aircraftINASA-TM-84270] p 461 N83-26845

APPROXIMATIONComputation of incompressible potential flow over an

airfoil using a high order aerodynamic panel method basedon circular arc panels[AD-A124896] p 428 N83-26825

ARIZONAA survey of helicopter and ambient urban noise levels

in Phoenix, Arizona[AD-A123856] p 479 N83-26322

ARMED FORCES (UNITED STATES)USAF mobility requirements — USER



ATMOSPHERIC CHEMISTRYHigh altitude let fuel photochemistry

[AD-A125035] p 471 N83-27035ATMOSPHERIC EFFECTS

Effect of humidity on jet engine axial-flow compressorperformance p 448 A83-35856

ATOMIC CLOCKSPhase 2A bench model development tactical rubidium

frequency standard[AD-A124462] p 477 N83-25990

ATOMIZERSEffect of air, liquid and miector geometry variables upon

the performance of a plain-jet airblast atomizerp 473 A83-35809

ATOMIZINGThe effect of fuel atomization on soot-free combustion

in a prevaponzmg combustor p 446 A83-35812ATTACK AIRCRAFT


ATTITUDE INDICATORSTheory underlying the peripheral vision horizon device

[ADA124426] p 445 N83-25710AUTOMATIC CONTROL


Automatic control and data acquisition system forcombustion laboratory applications[AD-A125195] p 470 N83-25829

AUTOMATIC FLIGHT CONTROLUsing adaptive control to synthesize invariant and

partially autonomous automatic stabilization systemsp 460 A83-33900

Flight management concepts development for fuelconservation p 447 A83-35843

AVIONICSReal time simulation of mission environments for

avionics systems integration[AIAA PAPER 83-1097] p 463 A83-36217

General aviation activity and avionics survey[AD-A124595] p 416 N83-25653

The remote link unit A demonstration of operationalperformance Part 3 Design manual Volume 2Appendices A - C[AD-A124622] p 476 N83-25935

The remote link unit A demonstration of operationalperformance, part 1[AD-A124619] p 476 N83-25939

Analysis of F-16 radar discrepancies[AD-A124749] p 476 N83-25948

Phase 2A bench model development tactical rubidiumfrequency standard[AD-A124462] p 477 N83-25990

A review and comparison of lightning return strokemodels using experimental data[AD-A124680] p 479 N83-26345

High-gam error actuated flight control systems forcontinuous linear multivanable plants[AD-A124871] p 462 N83-26848

AXIAL FLOWThe use of vortex generators as inexpensive compressor

casing treatment p 459 N83-26798End wall flow characteristics and overall performance

of an axial flow compressor stage[NASA-CR-3671 ] p 427 N83-26819

Finite element program for calculating flows inturbomachmes with results for NASA task-1 compressor[AD-A124987] p 460 N83-26841

AXIAL FLOW TURBINESAerodynamic optimization theory of A 3-D axial-flow

rotor-blading via optimal control p418 A83-35839A comprehensive method for preliminary design

optimization of axial gas turbine stages II - Codeverification[AIAA PAPER 83-1403] p 456 A83-36393

Investigation of the coupling of unsteady lift to low orderacoustic duct modes in an axial flow fan[AD-A124819] p 483 N83-27796

AXISYMMETRIC BODIESSingle- and multiple-crater induced nosetip transition

p420 A83-36078

BB-52 AIRCRAFT

Use of flight test results to improve the flying qualitiessimulation of the B-52H weapon system trainer[AIAA PAPER 83-1091] p 437 A83-36215

BALL BEARINGSHybnd hydrostatic/ball beanngs in high speed

turbomachmery[NASA-CR-168124] p 478 N83-27213

BASIC (PROGRAMMING LANGUAGE)Statistical study of TBO and estimation of acceleration

factors of ASMT for aircraft turbo-engine - AcceleratedSimulated Mission Endurance Testing

P448 A83-35858BATHYMETERS

Laser safety of air bathymetry[FOA-C-30292-E1] p 478 N83-27210

BEARINGLESS ROTORSCorrelation and evaluation of mplane stability

characteristics for an advanced beanngless mam rotor[NASACR-166448] p 440 N83-25695

BENDINGResonance tests on the tail of a CT4 aircraft

[ADA124566] p 441 N83-25703BIBLIOGRAPHIES

Foreign Technology Alert - Bibliography Transportationsafety[PB83-101659] p430 N83-25686

BLADE SLAP NOISEFull-scale measurements of blade vortex interaction

noise p 482 A83-33505Full-scale measurements of blade-vortex interaction

noise p 435 A83-35947BLADE TIPS

Numerical calculations of time dependentthree-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-11711 P 420 A83-36258

Aerodynamic research on Tipvane windturbines[PB83-147413] p 479 N83-27476

SLOWDOWN WIND TUNNELSSingle- and multiple-crater induced nosetip transition

p 420 A83-36078BLOWING

Experimental investigation of the effects of wall suctionand blowing on the performance of highly offsetdiffusers[AIAA PAPER 83-1169] p 423 A83-36922

BLOWOUTSCoaxial dump combustor investigations

p 459 N83-26791BLUNT BODIES

Single- and multiple-crater induced nosetip transitionp 420 A83-36078

Wind tunnel test of a C-18 aircraft modified with theadvanced range instrumentation aircraft radome[AD-A124771] p 425 N83-25671

BODY-WING AND TAIL CONFIGURATIONSForce and pressure measurements on a research model

with a low-, mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p 425 N83-25676

BODY-WING CONFIGURATIONSNumerical calculation of nonlinear aerodynamics of

wing-body configurations p 420 A83-36076Higher-order computational methods for transonic

wing/body flowfields[AD-A124079] p426 N83-25679

BOEING AIRCRAFTLarge jet aircraft validation and demonstrations An

overview of Boeing experience[AIAA PAPER 83-1049] p 439 A83-36472

BOMBER AIRCRAFTFrom new technology development to operational

usefulness B 36, B-58, F-111/FB-111[AIA PAPER 83-1046] p415 A83-36459


BOUNDARY LAYER CONTROLExperimental investigation of the effects of wall suction

and blowing on the performance of highly offsetdiffusers[AIAA PAPER 83-1169] p 423 A83-36922

BOUNDARY LAYER EQUATIONSCalculation of boundary layers near the stagnation point

of an oscillating airfoil[NASA-TM-84305] p 478 N83-27148

BOUNDARY LAYER FLOWGust response prediction of an airfoil using a modified

von Karman-Pohlhausen technique[AD-A124716] p 461 N83-25718

BOUNDARY LAYER SEPARATIONA collection of papers m the aerospace sciences

[AD-A122667] p417 N83-26787Experimental studies of the separating confluent

boundary-layer Volume 1 Summary[NASA-CR-3655] p 427 N83-26822

BOUNDARY LAYER STABILITYNatural laminar flow data from full-scale flight and

wind-tunnel experiments p 422 A83-36409BOUNDARY LAYER TRANSITION


A-5

BOUNDARY LAYERS SUBJECT INDEX

BOUNDARY LAYERSPressures measured in flight on the aft fuselage and

external nozzle of a twin-|et fighter1NASA-TP-2017) p 424 N83-25665

A note on adaptive wind tunnels with imperfect controlp 466 N83-26792

End wall flow characteristics and overall performanceof an axial flow compressor stage[NASA-CR-3671] p 427 N83-26819

Calculation of boundary layers near the stagnation pointof an oscillating airfoilINASA-TM-84305] p 478 N83-27148

Implicit upwind methods for the compressibleNavier Stokes equations(NASA-TM-84364) p 478 N83-27149

BOUNDARY VALUE PROBLEMSImportance of inlet boundary conditions for numerical

simulation of combustor flows(AIAA PAPER 83-1263] p 454 A83-36314

BROKEN SYMMETRYForced and self-excited vibrations of gas-turbine

assemblies with perfect and perturbed symmetryp 458 A83-36791

BYPASS RATIOCost effective performance restoration of high by-pass

engines p 447 A83-35833Experimental results of a deflected thrust V/STOL

nozzle research program[NASA-TM-83069] p 423 N83-25657

C-135 AIRCRAFTKC-135/CFM56 re-engine - The best solution

(AIAA PAPER 83-1374] p 456 A83-36367NOVA 2S correlation with KC 135A fuselage shock tube

test results[AD-A124013J p466 N83-25732

Preliminary science report on the directional solidificationof hypereutectic cast iron during KC-135 low GmaneuversINASATM-82528] p 470 N83-25854

C-141 AIRCRAFTWind tunnel investigation of cargo extraction parachutes

in the wake of a Lockheed C-141B Starhfter aircraft(AD-A124523] p 425 N83-25675

CALCULATORSHand-held computer programs for preliminary helicopter

design[AD-A125036) p 481 N83-27624

CALENDARSAGARD Bulletin Meetings, publications, membership

[AGARD-BUL-83/1] p417 N83-26786CALIBRATING

Seven-hole cone probes for high angle flowmeasurement Theory and calibration

p 474 A83-36085CANADAIR AIRCRAFT

CF34 upgrades Challenger capabilitiesp 434 A83-35315

CANARD CONFIGURATIONSA wind tunnel study of the effects of a close-coupled

canard on the aerodynamic characteristics of aforward-swept wing in incompressible flow[AD-A124722] p 425 N83-25673

CANOPIESNet-skirt addition to a parachute canopy to prevent

inversion p 428 A83-36911CANTILEVER BEAMS

Design of dry-friction dampers for turbine bladesp 450 A83-35883

CARBON FIBERSStatus, trends and implications of carbon fiber material

use[PB83-147751] p 471 N83-26934

CASCADE FLOWProfile losses dunng the release of air onto the surface

of nozzle vanes p418 A83-35590Numerical computation of turbulent flow around the

spinner of a turbofan engine p 418 A83-35838Aerodynamic optimization theory of A 3-D axial-flow

rotor-bladmg via optimal control p418 A83-35839A contribution to the calculation of secondary flows in

an axial flow compressor p 419 A83-35852Effect of entry boundary layer thickness on secondary


High angle-of-attack cascade measurements andanalysis P419 A83-35875

Design of choking cascade turns(AD-A124792] p 477 N83-26023

CASCADE WIND TUNNELSHigh angle-of-attack cascade measurements and

analysis p419 A83-35875

CAST ALLOYSSIructural members made of high-strength cast



Preliminary science report on the directional solidificationof hypereutectic cast iron during KC-135 low-Gmaneuvers[NASA-TM-82528] p 470 N83-25854

CENTRAL PROCESSING UNITSThe remote link unit A demonstration of operational

performance, part 1[AD-A124619] p 476 N83-25939

CENTRIFUGAL COMPRESSORSContribution to centrifugal compresor impeller design

p 448 A83-35865The effect of variation of diffuser design on the

performance of centrifugal compressorsp448 A83-35866

NASA low-speed centrifugal compressor forfundamental research[AIAA PAPER 83-1351] p 464 A83-36353

NASA low-speed centrifugal compressor forfundamental research[NASA-TM-83398] p 424 N83-25662

CERTIFICATIONA contribution to airworthiness certification of gas turbine

disks p 449 A83-35872CHANNELS (DATA TRANSMISSION)

Analysis of a real-time application[AIAA PAPER 83-1088] p 480 A83-36212

CHEMICAL ATTACKFluoroelastomers — materials for hostile fluid

environments p 469 A83-36066CHEMICAL COMPOSITION

Effect of fuel composition on Navy aircraft engine hotsection components[AIAA PAPER 83-1147] p 450 A83-36244

CHEMICAL REACTIONSNew trends in combustion research for gas turbine

engines p 446 A83-35806CINEMATOGRAPHY

Precision navigational filmstrips for use in DOD aircraft[AD-A124761] p 432 N83-25688

CIRCULAR CYLINDERSComputation of incompressible potential flow over an


CIRCULATION CONTROL AIRFOILSAn experimental/analytical investigation into the

performance of a 20-percent thick, 8 5-percent cambered,circulation controlled airfoil[AD-A124732] p 441 N83-25701

CITIESA survey of helicopter and ambient urban noise levels


CIVIL AVIATIONAirline safety and labor relations law - Balancing rights

and responsibility p 484 A83-34475AISA - Program for automated treatment of aeronautical

data — for civil aviation applicationsP462 A83-35598

Concepts for a future joint airlift development program[AIAA PAPER 83-1591] p 429 A83-36951

Worldwide aviation outlook — for passenger and freighttraffic 1982-1992[AIAA PAPER 83-1597] p 429 A83-36952

FAA aviation forecasts Fiscal years 1983-1994[AD-A124611] P416 N83-25652


CLEAR AIR TURBULENCEAircraft accident report IBEX Corporation Gates Learjet

23, N100TA, Atlanta, near Savannah, Georgia, 6 May1982[PB83-910401] P430 N83-26827

CLIMATEClimatic laboratory survey Hughes YAH-64 helicopter

[AD-A124670] p 440 N83-25698CLIMBING FLIGHT

Airworthiness and flight characteristics test Part 2YAH-64 advanced attack helicopter[AD-A125270] p 442 N83-25705

COASTAL WATER'Larus' and 'VP-1' tested in winter 1982

p 485 A83-34859COAXIAL FLOW

The relationship between the aerodynamic and acousticcharacteristics of coaxial lets p 482 A83-35712

Coaxial dump combustor investigationsp 459 N83-26791

COCKPIT SIMULATORSAn algorithm of flight simulation on a dynamic stand of

Support type p 462 A83-34429Generating an out-the-wtndow cockpit image with the

lAPX 432[AD-A124852] p 466 N83-25735

COCKPITSFlight operations A study of flight deck management

— Book p 428 A83-33767Generating an oul-the window cockpit image with the

lAPX 432[AD-A124852] p 466 N83-25735

CODINGThe remote link unit A demonstration of operational

performance Part 3 Design manual Volume 2Appendices A - C(AD-A124622] p 476 N83-25935

COLLAPSEAnalysis of progressive collapse of complex structures

[AD-A125266] p 478 N83-27260COLLISION AVOIDANCE

Computer model of a collision-avoidance system for airtraffic control p 431 A83-35275

COMBATData base considerations for a tactical environment

simulation[AIAA PAPER 83-1099] p 463 A83-36219

Dynamics of air combat p416 A83-36914COMBUSTIBLE FLOW

Importance of inlet boundary conditions for numericalsimulation of combustor flowstAIAA PAPER 83-1263] p 454 A83-36314

COMBUSTIONInjection, atomization, ignition and combustion of liquid

fuels in high-speed air streams[AD-A125237] p 471 N83-27033

COMBUSTION CHAMBERSAcoustic modal analysis of a full-scale annular

combustor[AIAA PAPER 83-0760] p 481 A83-33486

Cross spectra between temperature and pressure in aconstant area duct downstream of a combustor[AIAA PAPER 83-0762] p 481 A83-33487

Temperature and composition measurements in aresearch gas turbine combustion chamber

p 445 A83-35790New trends m combustion research for gas turbine

engines p 446 A83-35806The effect of fuel atomization on soot-free combustion

in a prevaponzing combustor p 446 A83-35812Methanol combustion in a CF6I-80A engine combustor

[AIAA PAPER 83-1138] p 469 A83-36241Experiments in dilution jet mixing

[AIAA PAPER 83-1201] p 475 A83-36277Application of 3D aerodynamic/combustion model to

combustor primary zone study[AIAA PAPER 83-1265] p 454 A83-36316

A JT8D low emissions combustor by radial zoning[AIAA PAPER 83 1324] p 455 A83-36339

The performance of an annular vane swirler — to aidin modeling gas turbine combustor flowfields and swirlingconfined flow turbulence[AIAA PAPER 83-1326] p 455 A83-36340

Design of choking cascade turns[AD-A124792] p 477 N83-26023


COMBUSTION EFFICIENCYExperimental research of the mechanism of flame

stabilization in two phase mixture p 469 A83-35822Effect of fuel composition on Navy aircraft engine hot

section components[AIAA PAPER 83-1147) p 450 A83-36244

COMBUSTION PRODUCTSThe effects of fuel properties upon pollutants present

in gas turbine aero-engines p 469 A83 35813COMBUSTION TEMPERATURE

CARS temperature and species measurements inaugmented jet engine exhausts — Coherent Anti-StokesRaman Spectroscopy[AIAA PAPER 83-1294] p 455 A83-36328

COMMERCIAL AIRCRAFTFlight operations A study of flight deck management

- Book p 428 A83-33767Cruise missile propulsion versus commercial airliner

propulsion - Different challenges can produce similarengine cycles[AIAA PAPER 83-1176] p 451 A83-36261

COMPARISONFAA integrated noise model validation Analysis of air

earner flyovers at Seattle-Tacoma Airport[AD-A124097] p 479 N83-26320

COMPONENT RELIABILITYComponent life reduction due to use of AVGAS in gas

turbine engines p 449 A83-35869

A-6

SUBJECT INDEX CONTROL THEORY


COMPOSITE MATERIALSComposite material aircraft electromagnetic properties

and design guidelines[AD-A124016] p470 N83-25795

Transient heat flow along uni-directional fibers incomposites[AD-A122926] p 471 N83-26929

Status, trends and implications of carbon fiber matenaluse[PB83-147751] p 471 N83-26934

COMPOSITE STRUCTURESAdvanced manufactunng development of a composite

empennage component for L 1011 aircraft[NASA-CR-172658] p 440 N83-25692

Advanced manufacturing development of a compositeempennage component for L-1011 aircraft[NASA-CR-172659] p 440 N83-25693

Advanced manufacturing development of a compositeempennage component for L-1011 aircraft[NASA-CR-172657) p 440 N83-25694

Evaluation of low cost aluminum composites for aircraftengine structural applications[NASA-TM-83357] p 470 N83-25790

A parametric study of surface imperfections and smallcutouts in a composite panel[AD-A124739] p 470 N83-25793

COMPRESSIBLE BOUNDARY LAYERPrediction of stagnation flow heat transfer on

turbomachmery airfoils[AIAA PAPER 83-1173] p 420 A83-36259

COMPRESSIBLE FLOWThe aerodynamics ol hyposonic velocities (On flows with

low Mach numbers) p417 A83-35535Three-dimensional compressible viscous analysis of

mixer nozzles[AIAA PAPER 83-1401] p 422 A83-36391

Finite differecnce calcultion of an mviscid transonic flowover oscillating airfoils[AD-A123982] p 426 N83-25677

Implicit upwind methods for the compressibleNavier-StoKes equations[NASA-TM-84364] p 478 N83-27149

COMPRESSOR BLADESHigh angle-of-attack cascade measurements and

analysis p419 A83-35875Stress analysis of critical areas of low-pressure

compressor-disc assembly of a developmentalaero-engine p 449 A83-35880

COMPRESSOR EFFICIENCYExperimental study of a high-through-flow transonic axial

compressor stage p419 A83-35853Effect of humidity on jet engine axial-flow compressor

performance p 448 A83-35856Design and performance of a low aspect ratio, high tip

speed multi-stage compressor[AIAA PAPER 83-1161] p 451 A83-36253

COMPRESSORSThe performance of single-shaft gas turbine load

compressor auxiliary power units[AIAA PAPER 83-1159] p 451 A83-36251


COMPUTATIONAL FLUID DYNAMICSSemi implicit calculation method of the flow field in a

duct with the flame stabilized by a step — for aircraft enginecombustion chamber design p 446 A83-35820

Applications of computational techniques m the designof ramjet engines p418 A83-35828

Numerical computation of turbulent flow around thespinner of a turbofan engine p418 A83-35838

A contribution to the calculation of secondary flows inan axial flow compressor p 419 A83-35852

Evaluation of a surface panel method coupled withseveral boundary layer analyses[AIAA PAPER 83-0011 ] p 474 A83-36039

Numencal calculations of time dependentthree-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-1171] p 420 A83-36258

Aerodynamic design of propfan powered transports[AIAA PAPER 83-1213] p 437 A83-36285

Method for calculating effects of a propfan on aircraftaerodynamics at subsonic speeds[AIAA PAPER 83-1216] p 420 A83-36287

Importance ol inlet boundary conditions for numencalsimulation of combustor flows[AIAA PAPER 83-1263] p 454 A83-36314

Progress toward the analysts of complex propulsioninstallation flow phenomenon[AIAA PAPER 83-1367] p 421 A83-36363

PAN AIR applications to aero-propulsion integration[AIAA PAPER 83-1368] p 421 A83-36364

PANAIR Pilot Code application to subsonic nacelle typeinterior flows[AIAA PAPER 83-1369] p 421 A83-36365

Three-dimensional compressible viscous analysis ofmixer nozzles[AIAA PAPER 83-1401] p 422 A83-36391

Improved numerical method for unsteady lifting surfacesin incompressible flow p 422 A83-36917

Correction to the wing source velocity error inWoodward's USSAERO code p 423 A83-36920

An assessment of factors affecting prediction ofnear-field development of a subsonic VSTOL let incross-flow[AD-A124583] p 441 ' N83-25699

Generalization of the air |et propulsion systems, the 'N'flow turbo-jet engine[AD-A123932] p 459 N83-25715

A collection of papers in the aerospace sciencesIAD-A1226671 p417 N83-26787

COMPUTER AIDED DESIGNSurfaces in computer aided geometric design,

Proceedings of the Conference, Oberwolfach, WestGermany, April 25-30, 1982 p 480 A83-33613


p 431 A83-35090Monte Carlo simulation of the engine development

process[AIAA PAPER 83-1405] p 456 A83-36394

A collection of papers in the aerospace sciences[AD-A122667] p417 N83-26787


Hand-held computer programs for preliminary helicopterdesign[AD-A125036] p 481 N83-27624

COMPUTER AIDED MANUFACTURINGSurfaces in computer aided geometric design,

Proceedings of the Conference, Oberwolfach, WestGermany, Apnl 25-30. 1982 p 480 A83-33613

COMPUTER GRAPHICSSimulator performance definition by cue synchronization

analysis[AIAA PAPER 83-1092] p 463 A83-36216

Design of a real-time CGSI system[AIAA PAPER 83-1101 ] p 474 A83-36221

Generating an out-the-wmdow cockpit image with thelAPX 432[AD-A124852] p 466 N83-25735

An interactive bombing mission simulation with computergraphics interface[AD-A124661] p 481 N83-26637

COMPUTER PROGRAMSPANAIR Pilot Code application to subsonic nacelle type

interior flows[AIAA PAPER 83-1369] p 421 A83-36365


Modeling the helmet-mounted sight system[AD-A124681] p 444 N83-25709

Design analysis of a self-acting spiral-groove ring sealfor counter-rotating shafts[NASA-TP-2142] p 458 N83-25712

FAA integrated noise model validation Analysis of aircarrier flyovers at Seattle-Tacoma Airport[AD-A124097] p 479 N83-26320

Programs for the transonic wind tunnel data processinginstallation Part 10 Six component measurementsupdated[AD-A122248] p 427 N83-26824

Dynamic characteristics of aerial refueling systems[AD-A124770] p 442 N83-26830


COMPUTER SYSTEMS DESIGNAnalysis of a real-time application

[AIAA PAPER 83-1088] p 480 A83-36212COMPUTERIZED SIMULATION

Computer studies of ACV heave performance as afunction of vent valve control parameters

p460 A83-34854Computer studies of ACV heave dynamics stabilization

p486 A83-35055Computer model of a collision-avoidance system for air

traffic control p 431 A83-35275Numencal simulation of airfoil ice accretion

[AIAA PAPER 83-0112) p 428 A83-36042Numencal simulation of electrothermal de-icing

systems(AIAA PAPER 83-0114] p 428 A83-36043

Simulator fidelity and flight test data - Improving the flightperformance of the B-52H WST production unit flightstation simulator[AIAA PAPER 83-1075] p 436 A83-36204

Sinusoidal integration for simulation of second-ordersystems(AIAA PAPER 83-1086) p 480 A83-36210

Error sources in hybrid computer based flightsimulation[AIAA PAPER 83-1090) p 436 A83-362U

Compensation for time delay in flight simulatorvisual-display systems[AIAA PAPER 83-1080) p 464 A83-36222

Importance of inlet boundary conditions for numericalsimulation of combustor flows[AIAA PAPER 83-1263) p 454 A83-36314

Performance capability of a Compact MultimissionAircraft Propulsion Simulator[AIAA PAPER 83-1358) p 464 A83-36356

Monte Carlo simulation of the engine developmentprocess[AIAA PAPER 83-1405) p 456 A83-36394

Investigation of an improved finite element model for arepaired T-38 horizontal stabilizer flutter analysis usingNASTRAN[AD-A124741] p 461 N83-25717


Structural model tuning via vector optimization[AD-A124791] p 477 N83-26103


Dynamic characteristics of aerial refueling systems[AD-A 124770] p 442 N83-26830

Simulation program of rotary wings[FOA-C-30308-E1 ] p 443 N83-26836

CONDENSINGCondensation studies in cryogenic nitrogen

expansions p 465 N83-25720CONFERENCES

Canadian Symposium on Air Cushion Technology, 16th,Charlottetown, Prince Edward Island, Canada, October19-21, 1982, Preprints p 484 A83-34851

International Symposium on Air Breathing Engines, 6th,Pans, France, June 6-10, 1983, Symposium Papers

p 445 A83-35801Flight Simulation Technologies Conference, Niagara

Falls, NY, June 13-15, 1983, Collection of TechnicalPapers p415 A83-36203


Technical evaluation report on the Fluid Dynamics PanelSpecialists' Meeting on Prediction of Aerodynamic Loadson Rotorcraft[AGARD-AR-189] p 426 N83-25682

CONGRESSIONAL REPORTSA strategy is needed to deal with peaking problems at

international airports[GAO/GGO-83-4] p429 N83-25683


NASA authonzation for fiscal year 1984[GPO-19-200] p487 N83-27921

CONICAL BODIESSeparated flows on a concave conical wing

p418 A83-35707CONNECTORS

The remote link unit A demonstration of operationalperformance Part 2 User's manual[AD-A124620] p 476 N83-25938

CONSTRUCTIONMaterials and modelling technology for cryogenic

environment p 465 N83-25723CONTAMINATION

Determination of the sensitivity of U S Air Force aircrafthydraulic system components to paniculatecontamination p 475 A83-36910

CONTROL STICKSSimulator performance definition by cue synchronization

analysis[AIAA PAPER 83-1092] p 463 A83-36216

CONTROL THEORYInteractive fine-tuning of linear-quadratic governers by

selective and direct action on the poles of the controlsystem[ONERA, TP NO 1983-21] p 480 A83-36430

A modified algorithm for determining structuralcontrollability p 480 A83-36455

NASA propulsion controls research[NASA-TM-83343J p 458 N83-25711

High-gam error actuated flight control systems forcontinuous linear multwanable plants[AD-A124871] p 462 N83-26848

A-7

CONTROL UNITS (COMPUTERS) SUBJECT INDEX

CONTROL UNITS (COMPUTERS)Automatic control and data acquisition system for

combustion laboratory applications[AD-A125195] p 470 N83-25829

CONTROL VALVESComputer studies ol ACV heave performance as a

function of vent valve control parametersp 460 A83-34854

CONTROLLABILITYBring cohesion to handling-qualities engineering

p434 A83-35772A modified algorithm for determining structural

controllability p 480 A83 36455CONVECTIVE HEAT TRANSFER

Profile losses during the release of air onto the surfaceof nozzle vanes p 418 A83-35590

CONVERGENT NOZZLESJT150 1/2-scale nozzle let noise experiment and

comparison with predictionINASATM-83370] p 482 N83-27793

CONVERGENT-DIVERGENT NOZZLESA stattc investigation of yaw vectoring concepts on

two-dimensional convergent-divergent nozzles(AIAA PAPER 83-1288] p 421 A83-36324

COOLERSPreliminary investigation on the performance of


COOLINGEarly experience in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726COST ANALYSIS

A placement model for flight simulators[ AD A123782] p 466 N83-25730

COST EFFECTIVENESSCost effective performance restoration of high by-pass

engines p 447 A83-35833COST ESTIMATES


COST REDUCTIONStructural members made of high-strength cast


COUNTER ROTATIONDesign analysis of a self-acting spiral-groove nng seal

for counter-rotating shafts — o ring seals(AIAA PAPER 83-1134] p 474 A83-36239

COUNTINGStatistical review of counting accelerometer data for

Navy and Marine fleet aircraft[AD-A124966] p 443 N83-26834

COVERINGSThe use of vortex generators as inexpensive compressor

casing treatment p 459 N83-26798CRACK PROPAGATION

Residual life prediction for |et engine rotor disks atelevated temperature p 472 A83-33974

The effect of microstructure on the fatigue behavior ofNi base superalloys p 469 A83-36166

Life prediction for turbine engine componentsp474 A83-36174

LCC evaluation of advanced engine damage tolerancegoals for a hot-section disk -~- m aircraft engines[AIAA PAPER 83-1407] p 456 AB3-36396

CREW STATIONSSpace-station crew-safety requirements

p 467 A83-36408CRITERIA

Cntena for optimizing starting cycles for highperformance fighter engines[AIAA PAPER 83-1127] p 450 A83-36236

CROSS FLOWAn assessment of factors affecting prediction of

near-field development of a subsonic VSTOL jet incross-flow[AD-A124583] p 441 N83-25699

CRUISE MISSILESCruise missile propulsion versus commercial airliner


CRUISING FLIGHTApplication of maximum likelihood estimation to the

identification of the stability derivatives of a wide bodytransport aircraft p 460 A83-35121

CRYOGENIC EQUIPMENTEarly expenence in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726CRYOGENIC WIND TUNNELS


Condensation studies in cryogenic nitrogenexpansions p 465 N83-25720

Temperature response of a model to set-point changesand conditioning in ETW p 465 N83-25721

Materials and modelling technology for cryogenicenvironment p 465 N83-25723

Problems involved by the instrumentation and theconception of cryogenic tests p 465 N83-25725

CUESOld problem/new solutions - Motion cuing algorithms

revisited[AIAA 83-1082] p 480 A83-36223

CULTURE (SOCIAL SCIENCES)Transportation Energy Conservation Through Land Use

Planning[PB83-148387] p 475 N83-25919

CUTTERSVerification testing of an AH-1S Wire Strike Protection

System (WSPS)[AD-A123188] p 429 N83-25684

CYCLIC LOADSThe use of a structural model for determining the

adaptability curve for turbine disks in stress concentrationzones p445 A83-35039


CYLINDRICAL BODIESComputation of incompressible potential flow over an


DAMAGE ASSESSMENTLCC evaluation of advanced engine damage tolerance

goals for a hot-section disk — in aircraft engines[AIM PAPER 83-1407] p 456 A83-36396

Analysis of progressive collapse of complex structures[AD-A125266] p 478 N83-27260

DAMPERSDesign of dry-friction dampers for turbine blades

p 450 A83-35883DAMPING

Optimum wire screens for control of turbulence in windtunnels p417 A83-33772

Damping seal for turbomachmery[NASA-CASE-MFS-25842-1] p 477 N83-26080

DATA ACQUISITIONAutomatic control and data acquisition system for

combustion laboratory applications[AD-A125195] p 470 N83-25829

FAA integrated noise model validation Analysis of aircarrier flyovers at Seattle Tacoma Airport[AD-A124097] p 479 N83-26320

Development of an oculometer data collectionsubsystem[AD-A124700] p 481 N83-26501

DATA BASE MANAGEMENT SYSTEMSResearch and analysis of head-directed area-of-mterest

visual system concepts[NASA-CR-166480] p 467 N83-26849

DATA BASESData base considerations for a tactical environment


Research and analysis of head-directed area-of-mterestvisual system concepts[NASA-CR-166480] p 467 N83-26849

DATA CORRELATIONCorrelation and evaluation of mplane stability

charactenstics for an advanced beanngless main rotor[NASA-CR-166448] p 440 N83-25695

DATA LINKSThe remote link unit A demonstration of operational

performance Part 3 Design manual, volume 1[AD-A124621] p 476 N83-25934




DATA PROCESSINGAISA - Program for automated treatment of aeronautical

data — for civil aviation applicationsp 462 A83-35598

Programs for the transonic wind tunnel data processinginstallation Part 10 Six component measurementsupdated[AD-A122248] p 427 N83-26824

DATA REDUCTIONDevelopment of an oculometer data collection

subsystem[AD-A124700] p 481 N83-26501

DE HAVILLAND AIRCRAFTThe Dash 8 development program

p 433 A83-33546DECONTAMINATION

Spectral decontamination of a real-time helicoptersimulation[AIAA PAPER 83-1087] p 436 A83-36211

DEFECTSA parametric study of surface imperfections and small

cutouts in a composite panel[AD-A124739] p 470 N83-25793

DEFENSE PROGRAMConcepts for a future joint airlift development program

[AIAA PAPER 83-1591] p 429 A83-36951DEFLECTION

Experimental results of a deflected thrust V/STOLnozzle research program[NASA-TM-83069] p 423 N83-25657

DEGREES OF FREEDOMCoupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 435 A83-35948DEICERS

Numerical simulation of electrothermal de-icingsystems(AIAA PAPER 83-0114] p 428 A83-36043

DELTA WINGSTemperature response of a model to set-point changes

and conditioning in ETW p 465 N83-25721DEMOGRAPHY

Transportation Energy Conservation Through Land UsePlanning[PB83-148387] p 475 N83-25919

DEPLOYMENTOperational deployment of the air cushion vehicle

p 485 A83-34864DESCENT TRAJECTORIES

Description of the computations and pilot proceduresfor planning fuel-conservative descents with a smallprogrammable calculator[NASA-TM-85642] p 444 N83 25707

DESIGN ANALYSISNew concept in hovercraft design diesel versus gas

turbines p 485 A83-34860ACV lift air systems - More puff for less power

p 485 A83-34861AP 1-88 craft 001 prototype clearance trials

p485 A83-34862Developments m air cushion vehicle spray

suppression p 486 A83-35056A design synthesis model for ACV/SES lift systems

p486 A83-35057Experimental study of a high-through-flow transonic axial

compressor stage p419 A83 35853Contribution to centrifugal compresor impeller design

p 448 A83-35865A comprehensive method for preliminary design

optimization of axial gas turbine stages II - Codevenlication[AIAA PAPER 83-1403] p 456 A83-36393

Monte Carlo simulation of the engine developmentprocess[AIAA PAPER 83-1405] p 456 A83-36394


DIESEL ENGINESNew concept in hovercraft design diesel versus gas

turbines p 485 A83-34860An update on high output lightweight diesel engines for

aircraft applications[AIAA PAPER 83-1339] p 458 A83-36925

DIESEL FUELSEmergency fuels technology

[AD-A125275] p 471 N83-25904DIFFERENTIAL EQUATIONS

Integra-differential equations of the dynamics of elasticsystems in nonstationary flows — flight vehicle dynamicsin turbulent nonseparated flow p 474 A83-35933

DIFFUSERSThe effect of variation of diffuser design on the

performance of centnfugal compressorsp448 A83-35866


DIFFUSIONAdvances in ejector technology A tribute to Hans von

Oham's vision p 477 N83-26805DIGITAL SYSTEMS


A-8

SUBJECT INDEX ENGINE DESIGN

Comparison ot an experience with full authority digitalengine controls in rotary wing and |et lift VSTOL aircraft[AIAA PAPER 83-12411 P 454 A83-36304


Digital flight control system validation[AD-A124506] p 462 N83-26847

DIRECTION FINDINGMultimode planar spiral for DF applications

p 430 A83-35089DIRECTIONAL SOLIDIFICATION (CRYSTALS)


DIRECTIONAL STABILITYAnalysis of nonplanar wing-tip-mounted lifting surfaces

on low-speed airplanes[NASA-CR-3684] p 424 N83-25667

DISORIENTATIONTheory underlying the peripheral vision horizon device

[AD-A124426] p 445 N83-25710DISPLAY DEVICES

Advanced display techniques for training themulti-member tactical air crew[AIAA PAPER 83-1079] p 443 A83-36207


Precision navigational filmstrips for use in DOD aircraft[AD-A124761] p 432 N83-25688

DISTORTIONDynamic distortion in a short s-shaped subsonic diffuser

with flow separation — Lewis 8 by 6 foot Supersonic WindTunnel[NASA-TM-84312] p 459 N83-26838

DOPPLER RADARNumerical treatment of Doppler radar signals — airport

radar, video data[ENSTE 82014] p 478 N83-27114

DRAG MEASUREMENTFriction drag measurements of acoustic surfaces

[AIAA PAPER 83 1356] p 422 A83-36414DRIFT

Investigation of a third order baro-damped verticlechannel of INS[AD-A124882] p 432 N83-26828

DROP SIZEEffect of air, liquid and injector geometry variables upon

the performance of a plam-iet airblast atomizerp 473 A83-35809


The effect of fuel atomization on soot free combustionin a prevaponzing combustor p 446 A83-35812

DRY FRICTIONDesign of dry-friction dampers for turbine blades

p 450 A83-35883DUCTED FANS

ACV lift air systems - More puff for less powerp485 A83-34861

DUCTED FLOWThe swirl in an S-duct of typical air intake proportions

p418 A83-35620Semi implicit calculation method of the flow field in a


DUCTSCross spectra between temperature and pressure in a

constant area duct downstream of a combustor[AIAA PAPER 83-0762] p 481 A83-33487

Early experience in using the Cryogenic Test Facilityat RAE Bedford, England p 465 N83-25726

DURABILITYDeterioration trending enhances jet engine hardware

durability assessment and part management[AIAA PAPER 83-1234] p 453 A83-36297

Development trends in engine durability - for USAFaircraft gas turbines[AIAA PAPER 83-1297] p 455 A83-36329

DUSTHigh temperature erosion study of INCO 600 metal

p 468 A83-35247DYNAMIC CHARACTERISTICS

Application of system identification flight analysistechniques to the pitch-heave dynamics of an air cushionvehicle p 484 A83-34852

Forced and self-excited vibrations of gas-turbineassemblies with perfect and perturbed symmetry

p 458 A83-36791DYNAMIC MODELS


Dynamic modeling of an air cushion vehiclep486 A83-35054

A dynamic model of turbojet in starting at high altitudep 447 A83-35846

DYNAMIC RESPONSECoupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 433 A83-33506Impact damping and airplane towing

p 428 A83-33625The response of aircraft to pulse excitation

p 434 A83-34312Coupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 435 A83-35948DYNAMIC STABILITY

An over-view of UTIAS research on the dynamic stabilityof air cushion vehicles p 484 A83-34853

Technical aspects of the AEROBAC AB-7p 484 A83-34858

Computer studies of ACV heave dynamics stabilizationp 486 A83-35055

DYNAMIC STRUCTURAL ANALYSISAdvanced manufacturing development of a composite

empennage component for L-1011 aircraft[NASA-CR-172659] p 440 N83-25693

ECONOMIC ANALYSISTransportation Energy Conservation Through Land Use

Planning[PB83-148387] p 475 N83-25919

ECONOMIC IMPACTStatus, trends and implications of carbon fiber material

use[PB83-147751] p 471 N83-26934

EFFICIENCYThe use of vortex generators as inexpensive compressor

casing treatment p 459 N83-26798EJECTION SEATS

ACES II negative Gz restraint investigation[AD-A124713] p 430 N83-25685

EJECTORSEntrainment and mixing in thrust augmenting ejectors

[AIAA PAPER 83-0172] p419 A83-36046Ejector nozzle test results at simulated flight conditions

for an advanced supersonic transport propulsion system[AIAA PAPER 83-1287] p 454 A83-36323

Advances in ejector technology A tribute to Hans vonChain s vision p 477 N83-26805

Model aerodynamic test results for a refined actuatedinlet ejector nozzle at simulated takeoff and cruiseconditions[NASA-CR-168051] p 426 N83-26816

ELASTIC BODIESIntegro-differential equations of the dynamics of elastic

systems in nonstationary flows — flight vehicle dynamicsin turbulent nonseparated flow p 474 A83-35933

ELASTIC DEFORMATIONNonlinear supersonic flutter of panels considering shear

deformation and rotary inertia p 473 A83-34315ELASTOMERS

Fluoroelastomers — materials for hostile fluidenvironments p 469 A83-36066

ELECTRIC CONTROLElectrohydraulic fuel-flow regulator for

gas-turbine-engine control systems p 458 A83-36793ELECTRIC FIELDS

A review and comparison of lightning return strokemodels using experimental data[AD-A124680] p 479 N83-26345

ELECTRICAL IMPEDANCEMultimode planar spiral for DF applications

p 430 A83-35089ELECTROMAGNETIC COMPATIBILITY

Composite material aircraft electromagnetic propertiesand design guidelines[AD-A124016] p470 N83-25795

ELECTROMAGNETIC FIELDSA review and comparison of lightning return stroke

models using experimental data[AD-A124680] p 479 N83-26345

ELECTRONIC CONTROLAdvanced propulsion controls - A total system view

p457 A83-36612ELECTRONIC COUNTERMEASURES

Survivabihty of interdiction aircraft Sensitivity to terrainfollowing, command altitude, velocity and electroniccounter measures[AD-A124870] p 443 N83-26833

ELECTRONIC MODULESThe remote link unit A demonstration of operational

performance Part 2 User's manual[AD-A124620] p 476 N83-25938

ELECTRONIC WARFARENew advances in wide band dual polarization antenna

elements for EW applications p 430 A83-35087

ELEVATORS (LIFTS)Resonance tests on the tail of a CT4 aircraft

[AD-A124566] p 441 N83-25703EMERGENCIES


EMPLOYEE RELATIONSAirline safety and labor relations law - Balancing rights

and responsibility p 484 A83-34475ENERGY CONSERVATION


Description of the computations and pilot proceduresfor planning fuel-conservative descents with a smallprogrammable calculator[NASA-TM-85642] p 444 N83-25707

Transportation Energy Conservation Through Land UsePlanning[PB83-148387] p 475 N83-25919

ENGINE AIRFRAME INTEGRATIONProgress in propulsion system/airframe structural


Empennage/afterbody integration for single andtwin-engine fighter aircraft[AIAA PAPER 83-1126] p 420 A83-36235

Integrated propulsion-aircraft control evaluation for acurrent Navy fighter[AIAA PAPER 83-1236] p 453 A83 36299

PAN AIR applications to aero propulsion integration[AIAA PAPER 83-1368] p 421 A83-36364

Wind tunnel tests of over-the-wmg nacelles — supportedon'stub-wings' p 422 A83-36916

ENGINE CONTROLSome aspects of development of power plant optimum

control to increase aircraft fuel efficiencyp 447 A83-35841

Inlet, engine, airframe controls integration developmentfor supercruismg aircraft p 447 A83-35842




Comparison of an experience with full authority digitalengine controls in rotary wing and jet-lift VSTOL aircraft[AIAA PAPER 83-1241] p 454 A83-36304

Advanced propulsion controls - A total system viewp457 A83-36612

ENGINE DESIGNAR 318 - Italy's low-cost GA turboprop

p 445 ASS 35675Temperature and composition measurements in a

research gas turbine combustion chamberp 445 A83-35790

Applications of computational techniques in the designof ramjet engines p 418 A83-35828

Design and development of a small gasturbme engineResults today A basis for design criteria of a nextgeneration p 446 A83-35829

The effect of variation of diffuser design on theperformance of centrifugal compressors

p 448 A83-35866The performance of single shaft gas turbine load

compressor auxiliary power units[AIAA PAPER 83-1159] p 451 A83-36251



A Monte Carlo simulation of the engine developmentprocess[AIAA PAPER 83-1230] p 452 A83 36294


Application of 3D aerodynamic/combustion model tocombustor primary zone study[AIAA PAPER 83-1265] p 454 A83-36316

Instrumental problems in small gas turbine engines[AIAA PAPER 83-1293] p 444 A83-36327

Development trends in engine durability — for USAFaircraft gas turbines[AIAA PAPER 83-1297] p 455 A83-36329

A JT8D low emissions combustor by radial zoning[AIAA PAPER 83-1324] p 455 A83 36339

Compound cycle turbofan engine[AIAA PAPER 83-1338] p 455 A83-36346

A-9

ENGINE FAILURE SUBJECT INDEX

Development and application of a liquid cooled V-8piston engine for general aviation aircraftIAIAA PAPER 83-1342] p 455 A83-36347

KC-135/CFM56 re engine - The best solution[AIAA PAPER 83-1374] p 456 A83-36367



Design and development of a nozzle extendible exitconeIAIAA PAPER 83-1410] p 467 A83-36399





V/STOL status from the engine technology viewpointp458 A83-36912


ENGINE FAILUREThe influence of defects on the operational strength

of disks and wheels in engines p 472 A83-33964Statistical study of TBO and estimation of acceleration


p 448 A83 35858Life estimation methods of gas turbine rotating

components p 449 A83-35870A contribution to airworthiness certification of gas turbine

disks p 449 A83-35872A Monte Carlo simulation of the engine development




ENGINE INLETSVariation of rotor blade vibration due to interaction of

inlet and outlet distortion p 450 A83-35882Aircraft engine inlet pressure distortion testing in a

ground test facility[AIAA PAPER 83-1233] p 453 A83-36296

Response of a supersonic inlet to downstreamperturbations[AIAA PAPER 83-8017] p 422 A83-36403

Dynamic distortion in a short s-shaped subsonic diffuserwith flow separation — Lewis 8 by 6 foot Supersonic WindTunnel[NASA-TM-84312] p 459 N83-26838

ENGINE MONITORING INSTRUMENTSF/A-18A Inflight Engine Condition Monitoring System

(IECMS)[AIAA PAPER 83-1237] p 453 A83-36300



Comparison of an experience with full authority digitalengine controls in rotary wing and jet-lift VSTOL aircraft[AIAA PAPER 83-1241] p 454 A83-36304


ENGINE NOISEAcoustic modal analysis of a full-scale annular




A compact inflow control device for simulating flight fannoise[NASA-TM-83349] p 482 N83-26643

ENGINE PARTSInvestigation methods on residual stresses in aero

engines components p 449 A83-35879Life prediction for turbine engine components

p474 A83-36174


Deterioration trending enhances jet engine hardwaredurability assessment and part management[AIAA PAPER 83-1234] p 453 A83-36297

Advanced techniques for gas and metal temperaturemeasurements in gas turbine engines[AIAA PAPER 83-1291 ] p 444 A83-36325


ENGINE STARTERSCriteria for optimizing starting cycles for high

performance fighter engines[AIAA PAPER 83-1127] p 450 A83-36236

ENGINE TESTSDevelopment of a turbojet engine simulator for scale


Ground simulation of engine operation at altitudep 463 A83-35863

Simulation of advanced engine lubrication and rotordynamics systems - Rig design and fabrication[AIAA PAPER 83-1133] p 450 A83-36238

Methanol combustion in a CF6I-80A engine combustor[AIAA PAPER 83-1138] p 469 A83-36241



Aircraft engine inlet pressure distortion testing in aground test facility[AIAA PAPER 83-1233] p 453 A83-36296






New transformations of S4 Modane hypersonic windtunnel for ramjet missiles tests[ONERA, TP NO 1983-24] p 464 A83-36433

ENTHALPYThermodynamics of organic compounds

[AD-A125022] p 483 N83-27895ENTRAINMENT

A study of lean extinction limit for pilot flame holderp 469 A83-35821

Entramment and mixing in thrust augmenting ejectors[AIAA PAPER 83-0172] p419 A83-36046

ENVIRONMENT MANAGEMENTFAA integrated noise model validation Analysis of air

carrier flyovers at Seattle-Tacoma Airport[AD-A124097] p 479 N83-26320

ENVIRONMENTAL TESTSThe effect of microstructure on the fatigue behavior of

Ni base superalloys p 469 A83-36166Climatic laboratory survey Hughes YAH-64 helicopter

[AD-A124670] p 440 N83-25698EPOXY MATRIX COMPOSITES

A tubular braided composite mam rotor blade sparp 435 A83-35949

EROSIONHigh temperature erosion study of INCO 600 metal

p 468 A83-35247Effect of sand erosion on the performance deterioration


ERROR ANALYSISA theoretical framework for analysis of lateral position

errors in VOR jet-route systems p 431 A83-35273Error sources in hybrid computer based flight





ERRORSHigh-gain error actuated flight control systems for

continuous linear multivanable plants[AD-A124871] p 462 N83-26848

EVAPORATIONEarly experience in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726EVAPORATION RATE


EXHAUST DIFFUSERSDesign and development of a nozzle extendible exit

cone[AIAA PAPER 83 1410] p 467 A83-36399

EXHAUST EMISSIONThe effects of fuel properties upon pollutants present

in gas turbine aero-engines p 469 A83-35813A JT8D low emissions combustor by radial zoning

[AIAA PAPER 83-1324] p 455 A83 36339Status, trends and implications of carbon fiber material

use[PB83-147751] p 471 N83-26934


EXHAUST GASESThrust reverser exhaust plume Remgestion tests for a

STOL fighter model[AIAA PAPER 83-1229] p 452 A83-36293

EXHAUST NOZZLESA high speed wind tunnel test evaluation of STOL

dedicated advanced exhaust nozzle concepts[AIAA PAPER 83-1225] p 421 A83-36292


A static investigation of yaw vectoring concepts ontwo-dimensional convergent-divergent nozzles[AIAA PAPER 83-1288] p 421 A83-36324

Three-dimensional compressible viscous analysis ofmixer nozzles[AIAA PAPER 83 1401 ] p 422 A83-36391

Definition of vectored nonaxisymmetnc nozzle plumes— for aircraft thrust vector control[AIAA PAPER 83-1290] p 423 A83-36924

Thrust performance of a variable-geometry, divergentexhaust nozzle on a turbojet engine at altitude[NASA-TP-2171] p459 N83-26839

EXTRACTIONWind tunnel investigation of cargo extraction parachutes


F-111 AIRCRAFTFrom new technology development to operational

usefulness B-36, B-58, F-111 /FB-111[AIA PAPER 83-1046] p415 A83-36459

AFTI/F-111 mission adaptive wing technologydemonstration program[AIAA PAPER 83-1057] p 438 A83-36468

F-14 AIRCRAFTIntegrated propulsion-aircraft control evaluation for a

current Navy fighter[AIAA PAPER 83-1236] p 453 A83-36299

F-14 rotary balance tests for an angle of-attack rangeof 0 deg to 90 deg[AD-A124468] p 441 N83-25700

F-16 AIRCRAFTThe F-16 - A technology demonstrator, a prototype, and

a flight demonstrator[AIAA PAPER 83-1063] p 438 A83-36467


F-18 AIRCRAFTFlight fidelity testing of the F/A-18 simulators

[AIAA 83-1094] p 437 A83-36225F/A-18A Inflight Engine Condition Monitoring System


F-4 AIRCRAFTAccelerated Mission Testing of the F110 Engine

[AIAA PAPER 83-1235] p 453 A83-36298F-5 AIRCRAFT


FACTOR ANALYSISAirframe RDTSE cost estimating A justification for and

development of unique cost estimating relationshipsaccording to aircraft type[AD-A123848] p417 N83-25656

A-10

SUBJECT INDEX FLIGHT SIMULATION

FAILURE ANALYSISThe influence ol defects on the operational strength

of disks and wheels in engines p 472 A83-33964Analysis of F-16 radar discrepancies

[AD-A124749] p 476 N83-25948FAILURE MODES


FAN BLADESContainment of turbine engine fan blades

p 449 A83-35871FAST FOURIER TRANSFORMATIONS

Numerical treatment of Doppler radar signals — airportradar, video data[ENST-E-82014) p 478 N83-27114

FATIGUE LIFEResidual life prediction for |el engine rotor disks at

elevated temperature p 472 A83-33974On improving the fatigue performance of a double-shear

lap |0mt p 473 A83-34744Life estimation methods of gas turbine rotating

components p 449 A83-35870Investigation methods on residual stresses in aero

engines components p 449 A83-35879Life prediction tor turbine engine components

p 474 A83-36174In-flight computation of helicopter transmission fatigue

life expenditure p 439 A83-36921FATIGUE TESTS

Evaluation of the effect ol voids in composite mam rotorblades p 472 A83-33507

Canadian forces tracker aircraft full-scale fatigue testat the national aeronautical establishment

p 433 A83-33548On improving the fatigue performance of a double-shear

lap |0int p 473 A83-34744Evaluation of the effect of voids in composite mam rotor

blades p 435 A83-35950FATTY ACIDS


p 468 A83-34500FEASIBILITY ANALYSIS

Feasibility of dry lubrication for limited-duty gas turbineengines[AIAA PAPER 83-1130] p 475 A83-36405

Feasibility study of three-dimensional holographicmterferometry for aerodynamics[NASA-CR-166483] p 483 N83-27845

FEDERAL BUDGETSNASA authorization for fiscal year 1984

[GPO-19-200] p487 N83-27921FEEDBACK CONTROL



p 461 A83-35773High-gam error actuated flight control systems for

continuous linear multivariable plants(AD-A124871] p 462 N83-26848

FIBER REINFORCED COMPOSITESEvaluation of the effect of voids in composite mam rotor

blades p 472 A83-33507Evaluation of the effect of voids in composite main rotor

blades p 435 A83-35950Light aircraft and sailplane structures in reinforced

plastics p 435 A83-36065FIGHTER AIRCRAFT

Aircraft design philosophy I - Lee Begin of Northropp434 A83-35624

Real time simulation of mission environments foravionics systems integration[AIAA PAPER 83 1097] p 463 A83-36217

Criteria for optimizing starting cycles for highperformance fighter engines[AIAA PAPER 83 1127] p 450 A83-36236

Thrust reverser exhaust plume Remgestion tests for aSTOL fighter model[AIAA PAPER 83-1229] p 452 A83-36293

A static investigation of yaw vectoring concepts ontwo-dimensional convergent-divergent nozzles[AIAA PAPER 83 1288] p 421 A83-36324



X-29 integrated technology demonstrator and ATF(AIAA PAPER 83 1058) p 438 A83-36469

GE's APG-67 - Fighter radar with a futurep432 A83-36625

Dynamics of air combat p416 A83-36914The future of the manned aircraft p416 A83-36960

The effects of the Production Oriented MaintenanceOrganization (POMO) concept on ADTAC aircraftmaintenance productivity and quality[ADA123981] p416 N83-25655

Pressures measured in flight on the aft fuselage andexternal nozzle of a twin-jet fighter[NASATP-2017] p 424 N83-25665


Effects of varying podded nacelle-nozzle installationson transonic aeropropulsive charactenstics of a supersonicfighter aircraft[NASA-TP-2120] p427 N83-26821



FILM COOLINGProfile losses during the release of air onto the surface

of nozzle vanes p 418 A83-35590FINITE DIFFERENCE THEORY

Application of a finite difference method to the transonicairfoil problem(AD-A124720) p 425 N83-25674

Higher-order computational methods for transonicwing/body flowfields[AD-A124079] p 426 N83-25679

FINITE ELEMENT METHODInvestigation of an improved finite element model for a

repaired T-38 horizontal stabilizer flutter analysis usingNASTRAN[AD-A124741] p 461 N83-25717




Finite element program for calculating flows inturbomachmes with results for NASA task-1 compressor[ADA124987] p 460 N83-26841


FINSThermal cycling in compact plate-fin heat exchangers

~ in aircraft gas turbines p 445 A83-34253Advanced manufacturing development of a composite

empennage component for L-1011 aircraft[NASACR-172657] p 440 N83-25694

FIRE CONTROLMicroprocessor-based optimal controllers for a

helicopter turret control system p 434 A83-35138GE's APG-67 - Fighter radar with a future

p432 A83-36625FIRING (IGNITING)

A dynamic model of turbojet in starting at high altitudep 447 A83-35846

FLAME HOLDERSFurther study on the prediction of liquid fuel spray capture

by v-gutter downstream of a plain orifice injector underuniform cross air flow p 473 A83-35810

A study of lean extinction limit for pilot flame holderp 469 A83-35821


FLAME STABILITYSemi implicit calculation method of the flow field in a


Experimental research of the mechanism of flamestabilization in two phase mixture p 469 A83-35822

FLAPS (CONTROL SURFACES)Wind tunnel investigation of varying hinged flaps

[ADA124703] p 424 N83-25668FLAT PLATES

Thermal cycling in compact plate-fin heat exchangers— in aircraft gas turbines p 445 A83-34253

FLEXIBLE WINGSStatic aeroelastic analysis of flexible wings via

NASTRAN, part 1[AD-A124662] p 477 N83-26099

FLIGHTGreater benefits to be gained from DoD flight

simulators[ADA123713] p 466 N83-25731

FLIGHT ALTITUDEOn the use of height rules in off-route airspace

p 431 A83-35274Survivability of interdiction aircraft Sensitivity to terrain


FLIGHT CHARACTERISTICSCF34 upgrades Challenger capabilities

p434 A83-35315In-flight simulation at the U S Air Force and Naval Test

Pilot Schools[AIAA PAPER 83-1078] p 436 A83-36206



A preliminary assessment of helicopter/VSTOL handlingqualities specifications[AD-A124667] p 461 N83-25716

FLIGHT CONDITIONSDynamics of air combat p 416 A83-36914Generalized maximum specific range performance

p439 A83-36918FLIGHT CONTROL

Aircraft active controls - New era in designp 461 A83-35773

Indoctrination of Navy test pilots to vectored thrust flightin the X-22A in-flight simulator[AIAA PAPER 83-1076] p 436 A83-36205


AFTI/F-111 mission adaptive wing technologydemonstration program[AIAA PAPER 83-1057] p 438 A83-36468

Digital flight control system validation[AD-A124506] p 462 N83-26847

High-gam error actuated flight control systems forcontinuous linear multivariable plants[AD-A124871] p 462 N83-26848

FLIGHT CREWSAirline safety and labor relations law - Balancing rights

and responsibility p 484 A83-34475FLIGHT HAZARDS

Scanning strategies for next generation weather radarsA study based on lifetimes of convective atmosphericphenomena hazardous to aviation[FAA-RD-82-69] p 476 N83-25929

Aircraft lightning-induced voltage test techniquedevelopments[ NASA CR 170403] p 442 N83-26829

FLIGHT OPERATIONSFlight operations A study of flight deck management

— Book p 428 A83-33767FLIGHT OPTIMIZATION

Advanced navigation systems and fuel conservationp428 A83-33545

FLIGHT PATHSComputer model of a collision-avoidance system for air

traffic control p 431 A83-35275All weather heliports and airway system - The future

need p 463 A83-36073An interactive bombing mission simulation with computer

graphics interface[AD-A124661] p 481 N83-26637

FLIGHT SAFETYAirline safety and labor relations law - Balancing rights

and responsibility p 484 A83-34475On the use of height rules in off-route airspace

p 431 A83-35274Space-station crew-safety requirements

p 467 A83-36408Flight tests of tow wire forces while flying a racetrack

pattern p 439 A83-36919FLIGHT SIMULATION

An algonthm of flight simulation on a dynamic stand ofsupport type p 462 A83-34429


Flight Simulation Technologies Conference, NiagaraFalls, NY, June 13-15, 1983, Collection of TechnicalPapers p 415 A83-36203


In-flight simulation at the U S Air Force and Naval TestPilot Schools[AIAA PAPER 83-1078] p 436 A83-36206

Sinusoidal integration for simulation of second-ordersystems[AIAA PAPER 83-1086] p"480 A83-36210



Error sources in hybnd computer based flightsimulation[AIAA PAPER 83-1090] p 436 A83-362U

A-11

FLIGHT SIMULATORS SUBJECT INDEX

Use of flight test results to improve the flying qualitiessimulation of the B-52H weapon system trainer| AIAA PAPER 83-1091] p 437 A83-36215

Real time simulation of mission environments foravionics systems integration| AIAA PAPER 83-1097] p 463 A83-36217

The man vehicle systems research facility A new NASAaeronautical R & D facility[AIAA PAPER 83-1098] p 463 A83 36218

Data base considerations for a tactical environmentsimulation| AIAA PAPER 83-1099] p 463 A83-36219

Ejector nozzle test results at simulated flight conditionsfor an advanced supersonic transport propulsion system[AIAA PAPER 83-1287] p 454 A83-36323

Dynamics of air combat p 416 A83-36914Greater benefits to be gained from DoD flight

simulators[AD-A123713] p 466 N83-25731

An interactive bombing mission simulation with computergraphics interface(AD-A124661) p 481 N83-26637

A compact inflow control device for simulating flight fannoiseINASATM-83349] p 482 N83-26643


FLIGHT SIMULATORSSimulator fidelity and flight test data - Improving the flight

performance of the B-52H WST production unit flightstation simulatorIAIAA PAPER 83-1075] p 436 A83-36204

Advanced display techniques for training themulti-member tactical air crew[AIAA PAPER 83-1079] p 443 A83-36207

Simulator performance definition by cue synchronizationanalysis[AIAA PAPER 83-1092] p 463 A83-36216

Design of a real time CGSI system[AIAA PAPER 83-1101] p 474 A83-36221

Compensation for time delay in flight simulatorvisual-display systems(AIAA PAPER 83-1080] p 464 A83-36222

Old problem/new solutions - Motion cuing algorithmsrevisited[AIAA 83-1082] p 480 A83-36223

Visually-coupled systems as simulation devices[AIAA 83-1083] p 464 A83-36224

Flight fidelity testing of the F/A-18 simulators[AIAA 83-1094] p 437 A83-36225

A placement model for flight simulators[AD-A123782] p 466 N83-25730

Simulator design features for carrier landing Part 2In-simulator transfer of training[ADA124024] p466 N83-25733

FLIGHT STABILITY TESTSA preliminary assessment of helicopter/VSTOL handling

qualities specifications[AD-A124667] p 461 N83-25716

FLIGHT TEST VEHICLESThe application of low-cost demonstrators for

advancead fighter technology evaluation[AIAA PAPER 83-1052] p 438 A83-36462

Aerospace technology demonstrators/research andoperational options[AIAA PAPER 83 1054] p 438 A83-36465

The Northrop Flying Wing prototypes[AIAA PAPER 83-1047] p 416 A83-36471

FLIGHT TESTSPerformance flight testing - Book

p 433 A83-33621Application of system identification flight analysis

techniques to the pitch-heave dynamics of an air cushionvehicle p 484 A83-34852

Simulator fidelity and flight test data • Improving the flightperformance of the B-52H WST production unit flightstation simulator[AIAA PAPER 83-1075] p 436 A83-36204

Use of flight test results to improve the flying qualitiessimulation of the B 52H weapon system trainer[AIAA PAPER 83-1091] p 437 A83-36215


Vanable sweep wing design(AIAA PAPER 83-1051] p 438 A83-36461


Large |et aircraft validation and demonstrations - Anoverview of Boeing experience[AIAA PAPER 83-1049] p 439 A83-36472


A technique to determine lift and drag polars in flightp422 A83-36913

Flight tests of tow wire forces while flying a racetrackpattern p 439 A83-36919

Experimental testing of flying qualities theories[AD-A124699] p 440 N83-25697

FLIGHT TRAININGIn-flight simulation at the U S Air Force and Naval Test

Pilot Schools[AIAA PAPER 83 1078] p 436 A83-36206

Advanced display techniques for training themulti-member tactical air crew(AIAA PAPER 83-1079] p443 A83-36207

FLOW CHARACTERISTICSNew trends in combustion research for gas turbine

engines p 446 A83-35806PANAIR Pilot Code application to subsonic nacelle type

interior flows[AIAA PAPER 83-1369] p 421 A83-36365

FLOW DISTORTIONThe prediction of performance of turbojet engine with

distorted inlet flow and its experimental studiesp 446 A83-35832

Variation of rotor blade vibration due to interaction ofinlet and outlet distortion p 450 A83-35882

Aircraft engine inlet pressure distortion testing in aground test facility(AIAA PAPER 83-1233] p 453 A83-36296

FLOW DISTRIBUTIONCalculation of subsonic flow past rectangular wings and

their combinations on the basis of a discrete vortexscheme p418 A83-35541

Semi implicit calculation method of the flow field in aduct with the flame stabilized by a step — for aircraft enginecombustion chamber design p 446 A83-35820

A study of lean extinction limit for pilot flame holderp469 A83-35821

Applications of computational techniques in the designof ramiet engines p418 A83-35828


Generalization of the air-jet propulsion systems, the 'N'flow turbo-jet engine(AD-A123932) p 459 N83-25715

FLOW EQUATIONSAn assessment of factors affecting prediction of


FLOW MEASUREMENTSeparated flows on a concave conical wing

p418 A83-35707The relationship between the aerodynamic and acoustic

characteristics of coaxial jets p 482 A83-35712Flow measurements within rotating stall cells in single

and multistage axial flow compressorsp419 A83-35873

Flow in rotating stall cells of a low speed axial flowcompressor p419 A83-35874

High angle-of-attack cascade measurements andanalysis p419 A83-35875


p 474 A83-36085NASA low-speed centrifugal compressor for

fundamental research[AIAA PAPER 83-1351] p 464 A83-36353

Aerodynamic measurements about a rotating propellerwith a laser velocimeter[AIAA PAPER 83-1354] p 421 A83-36355

FLOW RESISTANCEProfile losses during the release of air onto the surface

of nozzle vanes p418 A83-35590FLOW STABILITY

The aerodynamics of hyposonic velocities (On flows withlow Mach numbers) p417 A83-35535

FLOW VELOCITYThe aerodynamics of hyposonic velocities (On flows with

low Mach numbers) p417 A83-35535FLOW VISUALIZATION

Thrust reverser exhaust plume Remgestion tests for aSTOL fighter model[AIAA PAPER 83-1229] p 452 A83-36293


FLUID DYNAMICSTechnical evaluation report on the Fluid Dynamics Panel


Advances in ejector technology A tribute to Hans vonChain's vision p 477 N83-26805


FLUID INJECTIONThe distribution of the disperse fraction of a polydisperse

jet injected into a gas flow p 473 A83-34472Experiments in dilution jet mixing

[AIAA PAPER 83-1201] p 475 A83 36277FLUID MECHANICS



FLUID-SOLID INTERACTIONSRecent studies at NASA-Langley of vortical flows

interacting with neighboring surfacesp417 A83-33972

FLUORINE ORGANIC COMPOUNDSFluoroelastomers — materials for hostile fluid

environments p 469 A83-36066FLUTTER


Flutter prediction in forward-swept wings by assumedmodes and strip theory[AD-A124715] p461 N83-25719

Model mount system for testing flutter(NASA-CASE-LAR 12950-1] p 465 N83-25727

FORCED VIBRATIONExcitation and vibration of flexible bladed disks under

operating and simulated operation conditionsp 449 A83 35881


Design of dry friction dampers for turbine bladesp 450 A83-35883

Forced and self-excited vibrations of gas-turbineassemblies with perfect and perturbed symmetry

p 458 A83-36791FORECASTING

Worldwide aviation outlook — for passenger and freighttraffic 1982 1992[AIAA PAPER 83-1597] p 429 A83-36952

FAA aviation forecasts Fiscal years 1983-1994(AD-A124611) p416 N83 25652

FORTRANAn interactive bombing mission simulation with computer

graphics interlace[AD-A124661] p481 N83-26637

FRAGMENTATIONContainment of turbine engine fan blades

p 449 A83 35871FREE FLIGHT

Evaluation of aerodynamic derivatives from Do-28-TNTfree-flight model tests[ESA-TT-784] p 442 N83-25706

FREIGHTERSA new class ACV - Tanker freighter

p485 A83-35053FREQUENCIES


FREQUENCY RESPONSEResponse of a supersonic inlet to downstream

perturbations(AIAA PAPER 83-2017] p 422 A83-36403

FREQUENCY STANDARDSPhase 2A bench model development tactical rubidium

frequency standard[AO-A124462] p 477 N83-25990

FRICTION DRAGFriction drag measurements of acoustic surfaces

[AIAA PAPER 83 1356] p 422 A83-36414FUEL COMBUSTION

New trends in combustion research for gas turbineengines p 446 A83-35806

Methanol combustion in a CF6I-80A engine combustor[AIAA PAPER 83-1138] p 469 A83 36241


Application of 3D aerodynamic/combustion model tocombustor primary zone study1 AIAA PAPER 83-1265] p 454 A83-36316

Thermodynamics of organic compounds[AD-A125022] p 483 N83-27895

FUEL CONSUMPTIONAdvanced navigation systems and fuel conservation

p428 A83-33545New concept in hovercraft design diesel versus gas

turbines p 485 A83-34860Some aspects of development of power plant optimum



A-12

SUBJECT INDEX GROUND EFFECT MACHINES


Concepts for increased power and enhanced fuelconservation with newly patented multiple power-cycle gasturbine engines[AIAA PAPER 83-1209] p 452 A83-36282


FUEL FLOW REGULATORSElectrohydraulic fuel-flow regulator for

gas-turbine-engine control systems p 458 A83-36793FUEL INJECTION

Effect of air, liquid and miector geometry variables uponthe performance of a plain-jet airblast atomizer

p 473 A83-35809A JT8D low emissions combustor by radial zoning

[AIAA PAPER 83-1324) p 455 A83-36339FUEL OILS


FUEL PUMPSComponent life reduction due to use of AVGAS in gas

turbine engines p 449 A83-35869FUEL SPRAYS

Effect of air, liquid and injector geometry variables uponthe performance of a plain jet airblast atomizer

p 473 A83-35809Further study on the prediction of liquid fuel spray capture



The effect of fuel atomization on soot-free combustionin a prevaponzing combustor p 446 A83-35812

FUEL TESTSThe effect of products based on higher fatty acids on

the performance characteristics of jet fuelsp 468 A83-34500

Feasibility of a full-scale degrader for antimistmgkerosene[AIAA PAPER 83-1137] p 469 A83-36240


FUELSEmergency fuels technology

[AD-A125275] p 471 N83-25904An investigation of the effectiveness of smoke

suppressant fuel additives for turbojet applications[AD-A125025] p 471 N83-27034

FULL SCALE TESTSCanadian forces tracker aircraft full scale fatigue test


Full-scale measurements of blade-vortex jnteractionnoise p 435 A83 35947


FUSELAGESPressures measured in flight on the aft fuselage and

external nozzle of a twin-jet fighter[NASA-TP-2017] p 424 N83-25665

Wind tunnel investigation of cargo extraction parachutesin the wake of a Lockheed C 141B Starlifter aircraft[AD-A124523] p 425 N83-25675

Advanced manufacturing development of a compositeempennage component for U-1011 aircraft[NASA-CR-172659] p 440 N83-25693

NOVA-2S correlation with KC-135A fuselage shock tubetest results[AD-A124013] p466 N83-25732

Expenmental study of main rotor/tail rotor/airframeinteractions in hover Volume 1 Text and figures[NASA-CR-166485] p 427 N83-26820

GAS BEARINGSDesign analysis ot a self-acting spiral-groove ring seal

for counter-rotating shafts[NASA-TP-2142] p 458 N83-25712

GAS FLOWThe distribution of the disperse fraction of a polydisperse

jet injected into a gas flow p 473 A83-34472Early experience in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726GAS GENERATORS

Aspects of the T56 power section usage/operatingcosts[AIAA PAPER 83-1408] p 457 A83-36397

GAS MIXTURESA study of lean extinction limit for pilot flame holder

p 469 A83-35821

GAS TEMPERATUREEarly experience in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726Method of studying the operating temperature of gas

turbines — aeroengines[PNR-90159] p460 N83-26842

GAS TURBINE ENGINESThermal cycling in compact plate fin heat exchangers

— in aircraft gas turbines p 445 A83-34253Vibrational diagnostics of gas-turbine blades

P473 A83-35040Temperature and composition measurements in a



Effect of air, liquid and injector geometry variables uponthe performance of a plain-|et airblast atomizer

p 473 A83-35809The effects of fuel properties upon pollutants present

in gas turbine aero-engines p 469 A83-35813Experimental investigation on the role of flexbars and

metallic end seals in squeeze film dampers — of gas turbineengines p 473 A83-35862



A contribution to airworthiness certification of gas turbinedisks p449 A83-35872


Criteria for optimizing starting cycles for highperformance fighter engines[AIAA PAPER 83-1127] p 450 A83-36236

Eccentric end wear in cylindrical roller bearings can bepredicted and prevented[AIAA PAPER 83-1132] p 474 A83-36237


Advanced propfan engine characteristics andtechnology needs[AIAA PAPER 83-1155] p 450 A83-36250


Numerical calculations of time dependentthree-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-1171] p 420 A83-36258

A survey of trends in modern turbine technology[AIAA PAPER 83-1174] p 451 A83-36260

Experiments in dilution jet mixing[AIAA PAPER 83-1201] p 475 A83-36277




Importance of inlet boundary conditions for numericalsimulation of combustor flows[AIAA PAPER 83-1263] p 454 A83-36314







A comprehensive method for preliminary designoptimization of axial gas turbine stages II - Codeverification[AIAA PAPER 83-1403] p 456 A83-36393

The impact of engine usage on life cycle cost[AIAA PAPER 83-1406] p 456 A83-36395




Feasibility of dry lubrication for limited-duty gas turbineengines[AIAA PAPER 83-1130] p 475 A83-36405



Forced and self-excited vibrations of gas turbineassemblies with perfect and perturbed symmetry

p 458 A83-36791Electrohydraulic fuel-flow regulator for

gas-turbine-engine control systems p 458 A83-36793Method of studying the operating temperature of gas

turbines — aeroengines[PNR-90159] p460 N83 26842

GAS TURBINESFinite element program for calculating flows in

turbomachines with results for NASA task-1 compressor[AD-A124987] p 460 N83-26841

Experimental study of strength and existance domainof ground-to-air inlet vortices by ground board staticpressure measurements[PB83-144865] p 460 N83-26843

GASOLINEEmergency fuels technology

[AD-A125275] p 471 N83-25904GENERAL AVIATION AIRCRAFT

CF34 upgrades Challenger capabilitiesp 434 A83-35315


Analysis of nonplanar wing-tip-mounted lifting surfaceson low-speed airplanes[NASA-CR-3684] p 424 N83-25667


GLIDERSLight aircraft and sailplane structures in reinforced

plastics p 435 A83-36065GLOBAL POSITIONING SYSTEM

SH-3 helicopter/Global Positioning System integrationanalysis[AD-A125005] p 432 N83-25691

GRAPHITE-EPOXY COMPOSITESAdvanced manufacturing development of a composite

empennage component for L-1011 aircraft[NASA-CR-172658] p 440 N83 25692


GRAVITATIONStatistical review of counting accelerometer data for

Navy and Marine fleet aircraft[AD-A124966] p 443 N83-26834

GROOVESDesign analysts of a self-acting spiral-groove ring seal

for counter-rotating shafts — o ring seals[AIAA PAPER 83-1134] p 474 A83-36239

Design analysis of a self-acting spiral-groove ring sealfor counter-rotating shafts[NASA-TP-2142] p 458 N83-25712

GROUND EFFECT MACHINESCanadian Symposium on Air Cushion Technology, 16th,

Charlottetown, Prince Edward Island, Canada, October19-21, 1982, Prepnnts p 484 A83-34851

Application of system identification flight analysistechniques to the pitch-heave dynamics of an air cushionvehicle p 484 A83-34852

An over-view of UTIAS research on the dynamic stabilityof air cushion vehicles p 484 A83-34853


p 460 A83-34854How to improve air cushion vehicle performance with

VUMP equipped wave-forming keels — Vent-pumpp 484 A83-34855


'Larus' and 'VP-V tested in winter 1982p 485 A83-34859

New concept in hovercraft design diesel versus gasturbines p 485 A83-34860

ACV lift air systems - More puff for less powerp 485 A83-34861

AP 1-88 craft 001 prototype clearance trialsp 485 A83-34862

A-13

GROUND SUPPORT SYSTEMS SUBJECT INDEX

Operational deployment of the air cushion vehiclep 485 A83-34864

From Voyageur on - The exploitation of an opportunityto develop a Canadian air cushion vehicle industry —developing Canadian Air Cushion Vehicle Industry

p485 A83-35052A new class ACV - Tanker-freighter

p485 A83-35053Dynamic modeling of an air cushion vehicle

p 486 A83-35054Computer studies of ACV heave dynamics stabilization

p 486 A83-35055Developments in air cushion vehicle spray

suppression p 486 A83-35056A design synthesis model for ACV/SES lift systems

p486 A83-35057Skirts - Time for a new look' p 486 A83-35058The Transportation Development Centre contribution to

air cushion technology p 486 A83-35059LACV-30 supportablllty p 486 A83-35062Experimental analysis of the performance of an annular

peripheral jet vehicle in ground effect[AD-A124949] p 443 N83-26832

GROUND SUPPORT SYSTEMSAISA - Program for automated treatment of aeronautical


GROUND TESTSGround simulation of engine operation at altitude

p463 A83-35863GUIDE VANES


GUN TURRETSMicroprocessor-based optimal controllers for a

helicopter turret control system p 434 A83-35138GUSTS

Gust response prediction of an airfoil using a modifiedvon Karman Pohlhausen technique[AD-A124716] p 461 N83-25718

HH-53 HELICOPTER

The super stallion — CH-53E helicopter designfeatures p 435 A83-36075

HARDWAREDeterioration trending enhances jet engine hardware


HARDWARE UTILIZATION LISTSThe remote link unit A demonstration of operational

performance Part 3 Design manual Volume 2Appendices A - C[AD-A124622] p 476 N83-25935

HARMONIC GENERATIONSSpectral decontamination of a real-time helicopter


HARMONICSA note on adaptive wind tunnels with imperfect control

p 466 N83-26792HARRIER AIRCRAFT


HEAT BALANCETransient heat flow along uni-directional fibers in

composites[AD-A122926] p 471 N83-26929

HEAT EXCHANGERSThermal cycling in compact plate-fin heat exchangers

— in aircraft gas turbines p 445 A83-34253HEAT RESISTANT ALLOYS

High temperature erosion study of INCO 600 metalp468 A83-35247


HEAT SHIELDINGAerospace technology demonstrators/research and

operational options[AIAA PAPER 83-1054] p 438 A83-36465

HEAT TRANSFERThermal stability of alternative aircraft fuels

[AIAA PAPER 83-1143] p 470 A83-36243Prediction of stagnation flow heat transfer on



HEAT TRANSMISSIONTransient heat flow along uni-directional fibers in


HEAVINGApplication of system identification flight analysis



p 460 A83-34854Computer studies of ACV heave dynamics stabilization

p486 A83-35055HELICOPTER CONTROL

Microprocessor-based optimal controllers for ahelicopter turret control system p 434 A83-35138

HELICOPTER DESIGNA tubular braided composite mam rotor blade spar

p 435 A83-35949Evaluation of the effect of voids in composite mam rotor

blades p 435 A83-35950The super stallion — CH-53E helicopter design

features p 435 A83-36075The Ka-26 helicopter — Russian book

p437 A83-36448Hand-held computer programs for preliminary helicopter

design[AD-A125036] p 481 N83-27624

HELICOPTER ENGINESThe super stallion — CH-53E helicopter design

features p 435 A83-36075Accelerated simulated mission endurance test of a

turboshaft engine for military attack helicopterapplication[AIAA PAPER 83-1359] p 455 A83-36357

HELICOPTER PERFORMANCEThe Ka-26 helicopter — Russian book

p 437 A83-36448HELICOPTER PROPELLER DRIVE


HELICOPTER TAIL ROTORSExperimental study of mam rotor/tail rotor/airframe

interactions in hover Volume 1 Text and figures[NASA-CR-166485] p 427 N83-26820

HELICOPTER WAKESTechnical evaluation report on the Fluid Dynamics Panel


HELICOPTERSSpectral decontamination of a real-time helicopter




Ultrasonic weld bonding of helicopter primarystructures[AD-A124645] p 477 N83-26081

A survey of helicopter and ambient urban noise levelsin Phoenix, Arizona[AD-A123856] p 479 N83-26322

Sandra Helicopter Acoustic Detector (SHAD)[DE82-018925] p 483 N83-27803

HELIPORTSAll weather heliports and airway system - The future

need p 463 A83-36073HELMET MOUNTED DISPLAYS

Visually-coupled systems as simulation devices[AIAA 83-1083] p 464 A83-36224


HEWLETT-PACKARD COMPUTERSAutomatic control and data acquisition system for

combustion laboratory applications[AD-A125195] p470 N83-25829

HIGH ALTITUDEDesign and analysis of a subcntical airfoil for high

altitude, long endurance missions[AD-A124757] p 441 N83-25702

High altitude |et fuel photochemistry[AD-A125035] p 471 N83-27035

' HIGH ALTITUDE ENVIRONMENTSA dynamic model of turbojet in starting at high altitude

p447 A83-35846HIGH ALTITUDE TESTS


HIGH GAINHigh-gam error actuated flight control systems for

continuous linear multivanable plants[AD-A124871] p 462 N83-26848

HIGH LEVEL LANGUAGESHigher-order computational methods for transonic

wing/body flowfields[AD-A124079] p 426 N83-25679

HIGH SPEEDInjection, atomization, ignition and combustion of liquid


HIGH TEMPERATURE ENVIRONMENTSHigh temperature erosion study of INCO 600 metal

p 468 A83-35247HISTORIES

The history of V/STOL aircraft p 435 AS3-36074HOLE DISTRIBUTION (MECHANICS)


p 474 A83-36085HOLOGRAPHIC INTERFEROMETRY

Feasibility study of three-dimensional holographicmterierometry for aerodynamics[NASA-CR-166483] p 483 N83-27845

HORIZONTheory underlying the peripheral vision horizon device

[AD-A124426] p 445 N83-25710HORIZONTAL FLIGHT

Helicopter rotor toads using discretized matchedasymptotic expansions[NASA-CR-166092] p 423 N83-25658

Helicopter rotor loads using matched asymptoticexpansions User's manual[NASA-CR-166093] p 423 N83-25659

HOVERINGExperimental study of mam rotor/tail rotor/airframe


HUBSEffects of compressor hub treatment on stator stall

margin and performance[AIAA PAPER 83-1352] p 475 A83-36354

HUMAN FACTORS ENGINEERINGBring cohesion to handling-qualities engineering

p 434 A83-35772The man-vehicle systems research facility - A new NASA

aeronautical R & D facility[AIAA PAPER 83-1098] p 463 A83-36218

Foreign Technology Alert - Bibliography Transportationsafety[PB83-101659] p430 N83-25686


HUMIDITYEffect of humidity on jet engine axial-flow compressor

performance p 448 A83-35856HYBRID COMPUTERS

Error sources in hybrid computer based flightsimulation[AIAA PAPER 83-1090] p 436 A83-36214

HYDRAULIC CONTROLElectrohydraulic fuel-flow regulator for

gas-turbme-engme control systems p 458 A83-36793HYDROCARBON FUELS

The effect of fuel atomization on soot-free combustionin a prevaporizmg combustor p 446 A83-35812

HYDROCARBONSThermodynamics of organic compounds

[AD-A125022] p 483 N83-27895HYDROSTATICS

Hybrid hydrostatic/ball bearings in high-speedturbomachmery[NASA-CR-168124] p 478 N83-27213

HYPERSONIC AIRCRAFTThe future of the manned aircraft p416 A83-36960

HYPERSONIC HEAT TRANSFERTransient heat-transfer measurement technique in wind

tunnel and data analysis technique using systemidentification theory[AD-A124663] p 424 N83 25669

HYPERSONIC WIND TUNNELSNew transformations of S4 Modane hypersonic wind

tunnel for ramjet missiles tests[ONERA, TP NO 1983-24] p 464 A83-36433

ICESingle- and multiple-crater induced nosettp transition

p 420 A83-36078ICE FORMATION

Numerical simulation of airfoil ice accretion[AIAA PAPER 83-0112] p 428 A83-36042

Runway surface condition sensor specification guide[AC-150/5220-13A] p 465 N83-25728

IGNITIONInjection, atomization, ignition and combustion of liquid

fuels in high-speed air streams[AD-A125237] p 471 N83 27033

A-14

SUBJECTINDEX LANDING GEAR

IMAGE PROCESSINGDesign of a real-time CGSI system

[AIAA PAPER 83-1101] p 474 A83-36221IMPELLERS

Contribution to centrifugal compresor impeller designp448 A83-35865

Excitation and vibration of flexible bladed disks underoperating and simulated operation conditions

p 449 A83-35881IN-FLIGHT MONITORING

F/A-18A Inflight Engine Condition Monitoring System(IECMS)[AIAA PAPER 83-12371 p 453 A83-36300



INCINERATORSStatus, trends and implications of carbon fiber material

use[PB83-147751J p 471 N83-26934

INCOMPRESSIBLE FLOWImproved numerical method for unsteady lifting surfaces

in incompressible flow p 422 A83-36917Helicopter rotor loads using discretized matched

asymptotic expansions[NASA-CR-166092] p 423 N83-25658


A wind tunnel study of the effects of a close-coupledcanard on the aerodynamic characteristics of aforward swept wing in incompressible flow[AD-A124722] p 425 N83-25673

INDUSTRIESStatus, trends and implications of carbon fiber material

use[PB83-147751] p 471 N83-26934

INERTIANonlinear supersonic flutter of panels considering shear

deformation and rotary inertia p 473 A83-34315INERTIAL NAVIGATION

Investigation of a third order baro-damped verticlechannel of INS[AD-A124882] p 432 N83-26828

INFORMATION SYSTEMSAISA - Program for automated treatment of aeronautical


INFRARED IMAGERYSimulation program of rotary wings

[FOA-C-30308-E1] p 443 N83-26836INGESTION (ENGINES)

Thrust reverser exhaust plume Reingestion tests for aSTOL fighter model[AIAA PAPER 83-1229] p 452 A83-36293

Experimental study of strength and extstance domainof ground-to-air inlet vortices by ground board staticpressure measurements[PB83-144865] p 460 N83-26843

INJECTORSFurther study on the prediction of liquid fuel spray capture


INLET FLOWA study of lean extinction limit for pilot flame holder

p 469 A83-35821Applications of computational techniques in the design

of ramiet engines p418 A83-35828The prediction of performance of turbojet engine with

distorted inlet flow and its experimental studiesp446 A83 35832

Vanation of rotor blade vibration due to interaction ofinlet and outlet distortion p 450 A83-35882

Importance of inlet boundary conditions for numericalsimulation of combustor flows[AIAA PAPER 83-1263] p 454 A83-36314

Response of a supersonic inlet to downstreamperturbations[AIAA PAPER 83-2017] p 422 A83 36403


INLET NOZZLESModel aerodynamic test results for a refined actuated

inlet ejector nozzle at simulated takeoff and cruiseconditions[NASA-CR-168051] p 426 N83-26816

INLET PRESSUREAircraft engine tnlet pressure distortion testing in a


INLET TEMPERATUREA study of the response of a turbojet engine to the inlet

temperature transients p 448 A83-35849Coaxial dump combustor investigations

p 459 N83-26791INSPECTION

A strategy is needed to deal with peaking problems atinternational airports[GAO/GGD-83-4] p 429 N83-25683

INSTRUMENT ORIENTATIONPerformance capabilities of photographic flight


INTAKE SYSTEMSInvestigation of the coupling of unsteady lift to low order

acoustic duct modes in an axial flow fan[AD-A124819] p 483 N83-27796

INTEGRAL EQUATIONSIntegra-differential equations of the dynamics of elastic

systems in nonstationary flows -- flight vehicle dynamicsin turbulent nonseparated flow p 474 A83-35933

INTERACTIVE CONTROLInteractive fine-tuning of linear-quadratic governers by


INTERCEPTORSThe effects of the Production Oriented Maintenance

Organization (POMO) concept on ADTAC aircraftmaintenance productivity and quality[AD-A123981] p 416 N83-25655

INTERNAL PRESSURECoaxial dump combustor investigations

p 459 N83-26791INTERPOLATION

Surfaces in computer aided geometric design.Proceedings of the Conference, Oberwoltach, WestGermany, April 25-30, 1982 p 480 A83-33613

INVERSIONSNet-skirt addition to a parachute canopy to prevent

inversion p 428 A83-36911INVESTMENT CASTING


INVISCID FLOWApplications of computational techniques in the design

of ramjet engines p418 A83-35828Evaluation of a surface panel method coupled with

several boundary layer analyses[AIAA PAPER 83-0011 ] p 474 A83-36039

Finite differecnce calcultion of an inviscid transonic flowover oscillating airfoils[AD-A123982] p 426 N83-25677


IRON ALLOYSPreliminary science report on the directional solidification

of hypereutectic cast iron during KG-135 low-Gmaneuvers[NASA-TM-82528] p 470 N83-25854

ISENTROPIC PROCESSESCondensation studies in cryogenic nitrogen

expansions p 465 N83-25720ITERATION


JET AIRCRAFTLarge jet aircraft validation and demonstrations - An

overview of Boeing experience[AIAA PAPER 83-1049] p 439 A83-36472

JET AIRCRAFT NOISEA compact inflow control device for simulating flight fan

noise[NASA-TM-83349] p 482 N83-26643

JT150 1/2-scale nozzle jet noise experiment andcomparison with prediction[NASA-TM-83370] p 482 N83-27793


JET ENGINE FUELSThe effect of products based on higher fatty acids on

the performance characteristics of jet fuelsp468 A83-34500


High altitude jet fuel photochemistry[AD-A125035] p 471 N83-27035


JET ENGINESResidual life prediction for jet engine rotor disKs at

elevated temperature p 472 A83 33974Effect of humidity on jet engine axial-flow compressor

performance p 448 A83-35856Deterioration trending enhances jet engine hardware


CARS temperature and species measurements inaugmented |et engine exhausts — Coherent Anti-StokesRaman Spectroscopy[AIAA PAPER 83-1294] p 455 A83-36328

JET EXHAUSTCARS temperature and species measurements in

augmented jet engine exhausts -- Coherent Anti-StokesRaman Spectroscopy[AIAA PAPER 83-1294] p 455 A83-36328

Definition of vectored nonaxisymmetric nozzle plumes— for aircraft thrust vector control[AIAA PAPER 83-1290] p 423 A83-36924

JET FLOWThe distribution of the disperse fraction of a polydisperse

jet injected into a gas flow p 473 A83-34472An assessment of factors affecting prediction of


JET MIXING FLOWProfile losses during the release of air onto the surface

of nozzle vanes p 418 A83-35590The relationship between the aerodynamic and acoustic

characteristics of coaxial lets p 482 A83-35712Edge tones in high-speed flows and their application

to multiple-jet mixing p 482 A83-36077Experiments in dilution jet mixing

[AIAA PAPER 83-1201] p 475 A83-36277JET PROPULSION


Some historical trends in the research and developmentof aircraft[NASA-TM-84665] p 417 N83-26785

A collection of papers in the aerospace sciences[AD-A122667] p417 N83-26787

JP-4 JET FUELCoaxial dump combustor investigations

p 459 N83-26791

KEELSHow to improve air cushion vehicle performance with

VUMP equipped wave-forming keels — Vent-pumpp 484 A83-34855

KEROSENEFeasibility of a full-scale degrader for antimistmg

kerosene[AIAA PAPER 83-1137] p 469 A83-36240

Emergency fuels technology[AD-A125275J p 471 N83-25904


L-1011 AIRCRAFTAdvanced manufacturing development of a composite




LAMINAR FLOWNatural laminar flow data from full-scale flight and

wind-tunnel expenments p 422 A83-36409LAMINATES

Transient heat flow along uni-directional fibers incomposites[AD-A122926] p 471 N83-26929

LAND USETransportation Energy Conservation Through Land Use

Planning[PB83-148387] p 475 N83-25919


LANDING GEARThe response of aircraft to pulse excitation

p 434 A83-34312From new technology development to operational

usefulness B-36, B-58, F-111/FB-111[AIA PAPER 83-1046] p415 A83-36459

A-15

LANDING SIMULATION

LANDING SIMULATIONSimulator design features for carrier landing Part 2

In-simulator transfer of training[AD-A124024] p 466 N83-25733

LAP JOINTSOn improving the fatigue performance of a double-shear

lap |0int p 473 A83-34744LAPLACE TRANSFORMATION

Impact damping and airplane towingp 428 A83-33625

LASER APPLICATIONSLasers in aircraft construction — Russian book

p472 A83-34170Laser safety of air bathymetry

[FOA-C-30292-E1] p 478 N83-27210LASER DOPPLER VELOCIMETERS

Aerodynamic measurements about a rotating propellerwith a laser velocimeter[AIAA PAPER 83-1354] p 421 A83-36355

LASER INTERFEROMETRYFeasibility study of three-dimensional holographic

mterferometry for aerodynamics[NASA-CR-166483] p 483 N83-27845

LATERAL CONTROLLateral flying qualities of highly augmented fighter

aircraft, volume 1[AD-A118070] p443 N83-26835

LATERAL STABILITYApplication of maximum likelihood estimation to the


LATTICES (MATHEMATICS)Application of the vortex-lattice method to propeller

performance analysis[AD-A124837] p 459 N83-26840

LEADING EDGESRecent studies at NASA Langley of vortical flows


Prediction of stagnation flow heat transfer onturbomachinery airfoils[AIAA PAPER 83-1173] p 420 A83-36259

LEAR JET AIRCRAFTAircraft accident report IBEX Corporation Gates Leanet

23, N100TA, Atlanta, near Savannah, Georgia, 6 May1982[PB83-910401] p430 N83-26827

LIFE (DURABILITY)Scanning strategies for next generation weather radars

A study based on lifetimes of convective atmosphericphenomena hazardous to aviation[FAA-RD-82-69] p 476 N83-25929

LIFE CYCLE COSTSThe impact of engine usage on life cycle cost

[AIAA PAPER 83-1406] p 456 A83-36395LCC evaluation of advanced engine damage tolerance

goals for a hot-section disk - - in aircraft engines[AIAA PAPER 83-1407] p 456 A83-36396

LIFTApplications of advanced upper surface blowing

propulsive-lift technology[SAE PAPER 820956] p 433 A83-33628

How to improve air cushion vehicle performance withVUMP equipped wave forming keels — Vent-pump

p484 A83-34855ACV lift air systems - More puff for less power

p485 A83-34861A technique to determine lift and drag polars in flight

p422 A83-36913Theoretical determination of the lift of a simulated ejector

wing[AD-A124695] p 425 N83-25670

Design analysis of a self-acting spiral-groove ring sealfor counter-rotating shafts[NASA-TP-2142] p458 N83-25712


LIFT AUGMENTATIONTheoretical determination of the lift of a simulated ejector

wing[AD-A124695] p 425 N83-25670

LIFT DEVICESAnalysis of nonplanar wing-tip-mounted lifting surfaces


Theoretical determination of the lift of a simulated ejectorwing[AD-A124695] p 425 N83-25670

LIFT DRAG RATIORecent studies at NASA-Langley of vortical flows


SUBJECT INDEX

LIFTING BODIESTheoretical determination of the lift of a simulated ejector

wing[AD-A124695] p 425 N83-25670

LIGHT AIRCRAFTPerformance flight testing --- Book

p 433 A83-33621Light aircraft and sailplane structures in reinforced

plastics p 435 A83-36065LIGHTNING

A review and comparison of lightning return strokemodels using experimental data[AD-A124680J p 479 N83-26345

Aircraft lightning-induced voltage test techniquedevelopments[NASA-CR-170403] p 442 N83-26829


LINEAR POLARIZATIONNew advances in wide band dual polarization antenna

elements for EW applications p 430 A83 35087LINEAR SYSTEMS

Interactive fine-tuning of linear-quadratic governers byselective and direct action on the poles of the controlsystem[ONERA, TP NO 1983-21] p 480 A83-36430

LIQUID ATOMIZATIONInjection, atomization, ignition and combustion of liquid


LIQUID COOLINGDevelopment and application of a liquid-cooled V-a

piston engine for general aviation aircraft[AIAA PAPER 83 1342] p 455 A83-36347

LIQUID FUELSFurther study on the prediction of liquid fuel spray capture



Thermal stability of alternative aircraft fuels[AIAA PAPER 83 1143] p 470 A83-36243

Injection, atomization, ignition and combustion of liquidfuels in high-speed air streams[AD-A125237] p 471 N83-27033

LIQUID INJECTIONInjection, atomization, ignition and combustion of liquid


LOAD TESTSCanadian forces tracker aircraft full-scale fatigue test


High frequency fatigue of turbine blade material[AD-A124585] p 458 N83-25713

LOG PERIODIC ANTENNASA network formulation for phased arrays - Application

to log-periodic arrays of monopoles on curved surfacesp 431 A83-35090

LOG SPIRAL ANTENNASMultimode planar spiral for DF applications

p 430 A83-35089LONGITUDINAL STABILITY

Use of flight test results to improve the flying qualitiessimulation of the B-52H weapon system trainer[AIAA PAPER 83-1091] p 437 A83-36215

LOW COSTThe application of low-cost demonstrators for


LOW GRAVITY MANUFACTURINGPreliminary science report on the directional solidification

of hypereutectic cast iron during KC-135 low-Gmaneuvers[NASA-TM-82528] p 470 N83-25854

LOW SPEEDNASA low-speed centrifugal compressor for


LOW VISIBILITYGuidance control systems for aircraft on airport

surfaces[AIAA PAPER 83-1579) p 429 A83-36953

LUBRICANTSAir Force technical objective document FY 1984

[AD-A123961] p 487 N83-26783LUBRICATION SYSTEMS


Feasibility of dry lubrication for limited-duty gas turbineengines[AIAA PAPER 83-1130) p 475 A83-36405

MMAINTAINABILITY

Airframe RDT&E cost estimating A justification for anddevelopment of unique cost estimating relationshipsaccording to aircraft type[AD-A123848] p 417 N83-25656

MAINTENANCEThe effects of the Production Oriented Maintenance

Organization (POMO) concept on ADTAC aircraftmaintenance productivity and quality[AD-A123981] p416 N83-25655

MAN MACHINE SYSTEMSCompensation for time delay in flight simulator

visual-display systems[AIAA PAPER 83 1080] p 464 A83-36222


MANEUVERABILITYConfiguration development of a research aircraft with

post-stall maneuverability p 439 A83-36915MANEUVERABLE REENTRY BODIES

Aerospace technology demonstrators/research andoperational options[AIAA PAPER 83-1054] p 438 A83-36465

MANUAL CONTROLBring cohesion to handling-qualities engineering

P434 A83-35772MAPS

AISA Program for automated treatment of aeronauticaldata — for civil aviation applications

p 462 A83-35598MARINE PROPULSION


MASS FLOWAerodynamic research on Tipvane wmdturbmes

[PB83-147413] p 479 N83-27476MASS FLOW RATE

The transient performance of turbojet engines and axialcompressors p 447 A83-35847

MATERIALS SCIENCEHighly stressed materials, with aviation considered as

an example — Book p 467 A83-33951Materials in the mirror of aviation criteria

p 434 A83-33952Material, structural component, service life -- of aircraft

construction materials p 468 A83-33953Fluoroelastomers — materials for hostile fluid

environments p 469 A83-36066MATERIALS TESTS

The influence of defects on the operational strengthof disks and wheels in engines p 472 A83-33964

MATHEMATICAL MODELSMicroeconomic models for process development

p 472 A83-33650Dynamic modeling of an air cushion vehicle

p 486 A83-35054The prediction of performance of turbojet engine with

distorted inlet flow and its experimental studiesP446 A83-35832


Progress in propulsion system/airframe structuralintegration[AIAA PAPER 83-1123] p 437 A83 36234



MATRICES (MATHEMATICS)Static aeroelastic analysis of flexible wings via

NASTRAN, part 1[AO-A124662] p 477 N83 26099


MAXIMUM LIKELIHOOD ESTIMATESApplication of maximum likelihood estimation to the

identification of the stability derivatives of a wide bodytransport aircraft p 460 A8335121

METAL FATIGUEInvestigation methods on residual stresses in aero

engines components p 449 A83-35879The effect of microstructure on the fatigue behavior of

Ni base superalloys p 469 A83 36166High frequency fatigue of turbine blade material

[AD-A124585] P 458 N83-25713METAL MATRIX COMPOSITES

Evaluation of low cost aluminum composites for aircraftengine structural applications[NASA-TM-83357] p 470 N83-25790

METALLURGYHighly stressed materials, with aviation considered as

an example — Book p 467 A83 33951

A-16

SUBJECT INDEX NOZZLE GEOMETRY

METEOROLOGICAL RADARScanning strategies for next generation weather radars

A study based on lifetimes of convective atmosphericphenomena hazardous to aviation[FAA-RD 82-69] p 476 N83-25929

METHOD OF MOMENTSMultimode planar spiral for OF applications

p 430 A83-35089METHYL ALCOHOLS

Methanol combustion in a CF6I-80A engine combustor[AIAA PAPER 83-1138] p 469 A83-36241

MICROSTRUCTUREThe effect of mtcrostructure on the fatigue behavior of

Ni base superalloys p 469 A83-36166MILITARY AIRCRAFT

Vectored thrust afterbody nozzles for future combataircraft p 448 A83-35859

Data base considerations for a tactical environmentsimulation[AIAA PAPER 83-1099] p 463 A83-36219


The impact of engine usage on life cycle cost[AIAA PAPER 83-1406] p 456 A83-36395

Aircraft Prototype and Technology DemonstratorSymposium, Dayton, OH, March 23, 24, 1983,Proceedings P 415 A83-36457

Prototyping for fun and profit — military aircraft design[AIAA PAPER 83-1045] p 415 A83-36458



X-29 integrated technology demonstrator and ATF[AIAA PAPER 83-1058] p 438 A83-36469

MILITARY AVIATIONConcepts for a future joint airlift development program

[AIAA PAPER 83-1591] p 429 A83-36951USAF mobility requirements — USER


MILITARY HELICOPTERSMicroprocessor-based optimal controllers for a

helicopter turret control system p 434 A83-35138Accelerated simulated mission endurance test of a

turboshaft engine for military attack helicopterapplication[AIAA PAPER 83-1359] p 455 A83-36357

Climatic laboratory survey Hughes YAH-64 helicopter[AD-A124670] p 440 N83-25698


MILITARY OPERATIONSFAA aviation forecasts Fiscal years 1983-1994

[AD-A124611] p416 N83-25652The effects of the Production Oriented Maintenance

Organization (POMO) concept on ADTAC aircraftmaintenance productivity and quality[AD-A123981] P 416 N83-25655



MILITARY TECHNOLOGYDesign for testing of a low altitude night-in-weather

attack system[AIAA PAPER 83-1061] p 432 A83-36470

AFTI/F 16 technology demonstrator[AIAA PAPER 83-1059] p 439 A83-36474

MILITARY VEHICLESLACV-30 supportability p 486 A83-35062

MILLING (MACHINING)Microeconomic models for process development

p472 A83-33650MISSILE TESTS


MIXINGAdvances in ejector technology A tribute to Hans von

Cham's vision p 477 N83-26805MOBILITY

USAF mobility requirements - USERREQUIREMENTS[AIAA PAPER 83 1588] p 429 A83-36954

MODAL RESPONSEAcoustic modal analysis of a full-scale annular


MODULUS OF ELASTICITYEvaluation of low-cost aluminum composites for aircraft

engine structural applications[NASA-TM-83357] p 470 N83-25790

MOISTURE RESISTANCEFluoroelastomers — materials for hostile fluid

environments p 469 A83-36066MOMENTUM

End wall flow characteristics and overall performanceof an axial flow compressor stage[NASA-CR-3671 ] p 427 N83-26819

MONOPOLE ANTENNASA network formulation for phased arrays - Application


MONOPULSE ANTENNASComparative analysis of a phase and an amplitude


MONTE CARLO METHODA Monte Carlo simulation of the engine development

process[AIM PAPER 83-1230] p 452 A83-36294


MORPHOLOGYPreliminary science report on the directional solidification


MOTION SIMULATIONOld problem/new solutions - Motion cuing algorithms


MRCA AIRCRAFTA technique to determine lift and drag polars in flight

p422 A83-36913

NNACELLES

Progress toward the analysis of complex propulsioninstallation flow phenomenon[AIAA PAPER 83-1367] p 421 A83-36363


Effects of varying podded nacelle-nozzle installationson transonic aeropropulsive characteristics of a supersonicfighter aircraft[NASA-TP-2120] p 427 N83-26821

NASA PROGRAMSNASA authorization for fiscal year 1984

[GPO-19-200] p487 N83-27921NASTRAN


NATIONAL AIRSPACE UTILIZATION SYSTEMFAA's plan to improve the air traffic control system A

step in the right direction but improvements and bettercoordination are needed[GAO/AFMD-83-34] p 432 N83-25687

NAVIER-STOKES EQUATIONAn assessment of factors affecting prediction of

near-field development of a subsonic VSTOL |et incross-flow[AD-A124583] p 441 N83-25699


NAVIGATION AIDSPrecision navigational filmstrips for use m DOD aircraft

[AD-A124761] p 432 N83-25688Modeling the helmet-mounted sight system

[AD-A124681] p 444 N83-25709NAVIGATION INSTRUMENTS

Performance capabilities of photographic flightnavigation and sensor orientation systems

p431 A83-36122NETS

Net-skirt addition to a parachute canopy to preventinversion p 428 A83-36911

NETWORK SYNTHESISUsing adaptive control to synthesize invariant and

partially autonomous automatic stabilization systemsp460 A83-33900

NICKEL ALLOYSThe effect of microstructure on the fatigue behavior of

Ni base superalloys p 469 A83-36166NOISE INTENSITY


NOISE MEASUREMENTFull-scale measurements of blade-vortex interaction

noise p435 A83-35947In-flight acoustic test results for the SR-2 and SR-3

advanced-design propellers[AIAA PAPER 83-1214] p 452 A83-36286


NOISE POLLUTIONA survey of helicopter and ambient urban noise levels

in Phoenix, Arizona[AD-A123856] p 479 N83 26322


NOISE PREDICTION (AIRCRAFT)JT150 1/2-scale nozzle jet noise experiment and

comparison with prediction[NASA-TM-83370] p 482 N83-27793

NOISE REDUCTIONFriction drag measurements of acoustic surfaces

[AIAA PAPER 83-1356] p 422 A83-36414NOISE SPECTRA


NOISE TEMPERATURECross spectra between temperature and pressure in a

constant area duct downstream of a combustor[AIAA PAPER 83-0762] P 481 A83-33487

NONDESTRUCTIVE TESTSEvaluation of the effect of voids in composite mam rotor

blades p 472 A83-33507Evaluation of the effect of voids in composite mam rotor

blades p 435 A83-35950Life prediction for turbine engine components

p474 A83-36174Nondestructive evaluation methods for implementation

of damage-toleranl designed gas turbine enginecomponents[AIAA PAPER 83-1232] p 452 A83-36295

NONLINEAR FILTERSOld problem/new solutions - Motion cuing algorithms


NONLINEAR SYSTEMSThe response of aircraft to pulse excitation

p 434 A83-34312Numerical calculation of nonlinear aerodynamics of

wing-body configurations p 420 A83-36076NOSE TIPS


NOSES (FOREBODIES)Wind tunnel test of a C-18 aircraft modified with the

advanced range instrumentation aircraft radome[AD-A124771] p 425 N83-25671

NOZZLE DESIGNVectored thrust afterbody nozzles for future combat

aircraft p 448 A83-35859A high speed wind tunnel test evaluation of STOL



Design and development of a nozzle extendible exitcone[AIAA PAPER 83-1410] p 467 A83-36399


NOZZLE FLOWProfile losses during the release of air onto the surface

of nozzle vanes p 418 A83-35590Three-dimensional compressible viscous analysis of


Pressures measured in flight on the aft fuselage andexternal nozzle of a twin-jet fighter[NASA-TP-2017] p 424 N83-25665

A collection of papers in the aerospace sciences[AD-A122667] p 417 N83-26787

NOZZLE GEOMETRYEdge tones in high-speed flows and their application

to multiple-jet mixing p 482 A83-36077Definition of vectored nonaxisymmetnc nozzle plumes

— for aircraft thrust vector control[AIAA PAPER 83-1290] p 423 A83-36924

Pressures measured in flight on the aft fuselage andexternal nozzle of a twin-jet fighter[NASA-TP-2017] p424 N83-25665

A-17

NOZZLE THRUST COEFFICIENTS SUBJECT INDEX

Effect of empennage location on twin-engineafterbody-nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2 - wind tunnel tests[NASA-TP-2116] p424 N83-25666

NOZZLE THRUST COEFFICIENTSExperimental results of a deflected thrust V/STOL


NUMERICAL ANALYSISApplication of the vortex-lattice method to propeller


NUMERICAL CONTROLMicroprocessor-based optimal controllers for a

helicopter turret control system p 434 A83-35138Computer model of a collision-avoidance system for air

traffic control p 431 A83-35275Comparison of an experience with full authority digital

engine controls in rotary wing and |et-lift VSTOL aircraft[AIAA PAPER 83-1241] p 454 A83-36304

NUMERICAL INTEGRATIONSinusoidal integration for simulation of second-order


O RING SEALSDesign analysis of a self-acting spiral-groove ring seal

for counter-rotating shafts -- o ring seals[AIAA PAPER 83 1131] p 474 A83-36239

OCULOMETERSDevelopment of an oculometer data collection

subsystem[AD-A124700] p 481 N83-26501

OH-58 HELICOPTERA tubular braided composite mam rotor blade spar

p 435 A83-35949OMEGA NAVIGATION SYSTEM

Omega application in the Indonesian regionp 431 A83-35599

OMNIDIRECTIONAL ANTENNASA rapid-tuning high-power pod-mounted VHP antenna

system p 430 A83-35088ONBOARD DATA PROCESSING


OPERATING COSTSCost effective performance restoration of high by-pass

engines p 447 A83-35833Aspects of the T56 power section usage/operating

costs[AIAA PAPER 83-1405] p 457 A83-36397

OPERATING TEMPERATUREMethod of studying the operating temperature of gas


OPTICAL MEASURING INSTRUMENTSLasers in aircraft construction — Russian book

p472 A83-34170OPTIMAL CONTROL

Aerodynamic optimization theory of A 3-D axial-flowrotor-bladmg via optimal control p 418 A83-35839


p447 A83-35841Old problem/new solutions - Motion cuing algorithms



Investigation of a third order baro damped verticlechannel of INS[AD-A124882] p 432 N83-26828

OPTIMIZATIONOptimization for structures of discrete-size elements

P472 A83-34311Criteria for optimizing starting cycles for high



OSCILLATING FLOWFinite differecnce calcultion of an mviscid transonic flow

over oscillating airfoils[AD-A123982] p 426 N83-25677

OSCILLATIONSCalculation of boundary layers near the stagnation point


OZONEHigh altitude jet fuel photochemistry

[AD-A125035] p 471 N83-27035

PANEL METHOD (FLUID DYNAMICS)Evaluation of a surface panel method coupled with



PAN AIR applications to aero-propulsion integration[AIAA PAPER 83-1368] p 421 A83-36364


PANELSNonlinear supersonic flutter of panels considering shear

deformation and rotary inertia p 473 A83-34315Advanced manufacturing development of a composite



PARABOLIC DIFFERENTIAL EQUATIONSAn assessment of factors affecting prediction of

near-field development of a subsonic VSTOL |et incross flow[AD-A124583] p 441 N83-25699

PARACHUTE DESCENTThe motion dynamics of parachute systems — Russian

book p 422 A83-36450PARACHUTES

Net-skirt addition to a parachute canopy to preventinversion p 428 A83-36911


PARAMETER IDENTIFICATIONEvaluation of aerodynamic derivatives from Do-28-TNT

free-flight model tests[ESATT-784] p 442 N83-25706

PARAMETERIZATIONA small parameter method in problems of maneuvering



PARTICLE SIZE DISTRIBUTIONThe distribution of the disperse fraction of a polydisperse

jet injected into a gas flow p 473 A83-34472An investigation of the effectiveness of smoke


PASSENGER AIRCRAFTSAAB-Fairchild 340 - Transatlantic frontrunner

p 434 A83-35623The future of the manned aircraft p 416 A83-36960

PASSENGERSA strategy is needed to deal with peaking problems at

international airports[GAO/GGD-83-4] p 429 N83-25683

PAVEMENTSRunway surface condition sensor specification guide

[AC-150/5220-13A] p 465 N83-25728PERFORMANCE PREDICTION

On improving the fatigue performance of a double-shearlap joint p 473 A83-34744


p 460 A83-34854Technical aspects of the AEROBAC AB-7

p 484 A83-34858Further study on the prediction of liquid fuel spray capture


Further studies on the prediction of spray evaporationrates — for aircraft fuels p 468 A83 35811


p 446 A83-35832The transient performance of turbojet engines and axial

compressors p 447 A83-35847A study of the response of a turbojet engine to the inlet

temperature transients p 448 A83-35849Effect of sand erosion on the performance deterioration




Maximum loading capability of axial flow compressors[AIAA PAPER 83-1163] p 451 A83-36254

The performance of an annular vane swirler — to aidin modeling gas turbine combustor flowfields and swirlingconfined flow turbulence[AIAA PAPER 83-1326] p 455 A83 36340



Application of the vortex-lattice method to propellerperformance analysis[AD-A124837] p 459 N83-26840

PERFORMANCE TESTS'Larus' and 'VP-1' tested in winter 1982

p485 A83-34859AP 1-88 craft 001 prototype clearance trials

p 485 A83-34862Experimental investigation on the role of flexbars and


Contribution to centrifugal compresor impeller designp448 A83-35865



Effects of compressor hub treatment on stator stallmargin and performance[AIAA PAPER 83-1352] p 475 A83-36354



PERIPHERAL VISIONTheory underlying the peripheral vision horizon device

[AD-A124426] p 445 N83-25710PERTURBATION

Some recent applications of XTRAN3S[NASA-TM-85641 ] p 426 N83-26815

PHASED ARRAYSA network formulation for phased arrays - Application


PHOTOCHEMICAL REACTIONSHigh altitude jet fuel photochemistry

[AD-A125035] p 471 N83-27035PHOTOELASTIC ANALYSIS


PILOT ERRORModeling the helmet-mounted sight system

[AD-A124681] p 444 N83 25709PILOT PERFORMANCE

Flight operations A study of flight deck management— Book p 428 A83-33767

Bring cohesion to handling-qualities engineeringp 434 A83-35772

PILOT TRAININGA placement model for flight simulators

[AD-A123782] p 466 N83-25730Simulator design features for carrier landing Part 2

In-simulator transfer of training[AD-A124024] p 466 N83 25733

PILOTLESS AIRCRAFTA dynamic model of turbojet in starting at high altitude

p 447 A83-35846PILOTS (PERSONNEL)

Airline safety and labor relations law - Balancing rightsand responsibility p 484 A83-34475


PISTON ENGINESThe effect of vanation of diffuser design on the

performance of centrifugal compressorsp 448 A83-35866


PITCH (INCLINATION)Gust response prediction of an airfoil using a modified


A-18

SUBJECT INDEX QUALITY CONTROL

PITCHING MOMENTSEvaluation of aerodynamic derivatives from Do-28 TNT

free-flight model tests[ESA-TT-784] P442 N83-25706

PLASMA PHYSICSA collection of papers in the aerospace sciences

[AD-A122667 J p417 N83-26787PLASTIC DEFORMATION

The use of a structural model for determining theadaptability curve for turbine disks m stress concentrationzones p 445 A83-35039

PLATES (STRUCTURAL MEMBERS)Impact damping and airplane towing

p 428 A83-33625PLUMES

Thrust reverser exhaust plume Remgestion tests for aSTOL- fighter model[AIAA PAPER 83-1229] p 452 A83-36293

Definition of vectored nonaxisymmetric nozzle plumes— for aircraft thrust vector control[AIAA PAPER 83-12901 P 423 A83-36924

POLARIZATION CHARACTERISTICSNew advances in wide band dual polarization antenna

elements for EW applications p 430 A83-35087POLICIES

Concepts for a future pint airlift development program[AIAA PAPER 83-1591] p 429 A83-36951

POLLUTION CONTROLAn investigation of the effectiveness of smoke


POSITION (LOCATION)Precision navigational filmstnps for use in DOD aircraft

[AD-A124761] p432 N83-25688POSITION ERRORS

A theoretical framework for analysis of lateral positionerrors in VOR let-route systems p 431 A83-35273

POTENTIAL FLOWProgress toward the analysis of complex propulsion

installation flow phenomenon[AIAA PAPER 83-1367] p 421 A83-36363


Helicopter rotor loads using discretized matchedasymptotic expansions[NASA-CR-166092] p 423 N83-25658


POWER EFFICIENCYVectored thrust afterbody nozzles for future combat

aircraH p 448 A83-35859The aerodynamic design and performance of the

General Electric/NASA EEE fan — Energy EfficientEngine[AIAA PAPER 83-1160] p 451 A83-36252



PRECOOLINGProblems involved by the instrumentation and the

conception of cryogenic tests p 465 N83-25725PREDICTION ANALYSIS TECHNIQUES

Residual life prediction for jet engine rotor disks atelevated temperature p 472 A83-33974


Flutter prediction in forward-swept wings by assumedmodes and strip theory[AD-A124715] p 461 N83-25719


PREMIXED FLAMESSemi implicit calculation method of the flow field in a


PREPREGSAdvanced manufacturing development of a composite


PRESSURE DISTRIBUTIONVariation of rotor blade vibration due to interaction of

inlet and outlet distortion p 450 A83-35882Improved numerical method for unsteady lifting surfaces

in incompressible flow p 422 A83-36917Force and pressure measurements on a research model

with a low- mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p 425 N83-25676

Application of the vortex-lattice method to propellerperformance analysis[AD-A124837] p 459 N83-26840

PRESSURE EFFECTSExperimental investigation of the effects of wall suction


PRESSURE MEASUREMENTThe swirl in an S-duct of typical air intake proportions

p418 A83-35620Aircraft engine inlet pressure distortion testing in a



PRESSURE OSCILLATIONSResponse of a supersonic inlet to downstream

perturbations[AIAA PAPER 83-2017] p 422 A83-36403

PRESSURE RATIOExperimental results of a deflected thrust V/STOL


PRESSURE REDUCTIONAdvanced manufacturing development of a composite


PRESSURE SENSORSSeven-hole cone probes for high angle flow



PROCESS CONTROL (INDUSTRY)Microeconomic models for process development

p472 A83-33650PROCUREMENT

Airframe RDT&E cost estimating A tustification for anddevelopment of unique cost estimating relationshipsaccording to aircraft type[AD-A123848] p417 N83-25656

PRODUCT DEVELOPMENTMicroeconomtc models for process development

P472 A83-33650A Monte Carlo simulation of the engine development




PRODUCTION COSTSDevelopment and production cost estimating

relationships for aircraft turbine engines[AD-A123753] p 459 N83-25714

PRODUCTIVITYThe effects of the Production Oriented Maintenance


PROGRAM VERIFICATION (COMPUTERS)NASA low-speed centrifugal compressor for

fundamental research[AIAA PAPER 83-1351 ] p 464 A83-36353

PROJECT MANAGEMENTSAAB-Fairchild 340 - Transatlantic frontrunner

p 434 A83-35623Aircraft Prototype and Technology Demonstrator

Symposium, Dayton, OH, March 23, 24, 1983,Proceedings p415 A83-36457

PROP-FAN TECHNOLOGYProp-fan powered aircraft - An overview

[SAE PAPER 820957] p 434 A83-33629Advanced preplan engine characteristics and

technology needs(AIAA PAPER 83-1155] p 450 A83-36250


PROPAGATION MODESAcoustic modal analysis of a full-scale annular

combustor(AIAA PAPER 83-0760] p 481 A83-33486

PROPELLER BLADESApplication of the vortex-lattice method to propeller


PROPELLER EFFICIENCYProp-fan powered aircraft - An overview

[SAE PAPER 820957] p 434 A83-33629PROPELLER SLIPSTREAMS


PROPELLERSIn-flight acoustic test results for the SR-2 and SR-3


Aerodynamic measurements about a rotating propellerwith a laser velocimeter(AIAA PAPER 83-1354] p 421 A83 36355


PROPULSIONApplications of advanced upper surface blowing


PROPULSION SYSTEM CONFIGURATIONSAdvanced propfan engine characteristics and

technology needs[AIAA PAPER 83-1155] p 450 A83 36250


Generalization of the air iet propulsion systems, the 'N'flow turbo-jet engine[AO-A123932] p 459 N83-25715

PROPULSION SYSTEM PERFORMANCEOn the propulsion system of the NAL quiet STOL

research aircraft p 446 A83-35831Propulsion system simulation technique for scaled wind

tunnel model testing p 463 A83-35850Cruise missile propulsion versus commercial airliner

propulsion - Different challenges can produce similarengine cycles[AIAA PAPER 83-1176] p 451 A83 36261




Advanced propulsion controls - A total system viewp 457 A83-36612


PROPULSIVE EFFICIENCYConcepts for increased power and enhanced fuel

conservation with newly patented multiple power-cycle gasturbine engines[AIAA PAPER 83-1209] p 452 A83-36282


PROTECTIVE COATINGSAir Force technical objective document FY 1984

[AD-A123961] p487 N83-26783PROTOTYPES

AP 1-88 craft 001 prototype clearance trialsp 485 A83-34862


Prototyping for fun and profit — military aircraft design[AIAA PAPER 83-1045] p415 A83-36458

XB-70 technology advancements[AIAA PAPER 83-1048] p 437 A83 36460


The F-16 - A technology demonstrator, a prototype, anda flight demonstrator[AIAA PAPER 83-1063] p 438 A83-36467

The Northrop Flying Wing prototypes[AIAA PAPER 83-1047] p416 A83 36471

Large jet aircraft validation and demonstrations - Anoverview of Boeing experience[AIAA PAPER 83-1049) p 439 A83-36472

The F-5 story - Prototype and technologydemonstrator(AIAA PAPER 83-1062] p 439 A83-36473

PULSE DOPPLER RADARGE's APG-67 - Fighter radar with a future

p 432 A83-36625

QQUADRATIC EQUATIONS


QUALITY CONTROLSome applications of ultrasonic methods for the quality

control of nonmetallic objects p 475 A83-36794

A-19

RADAR EQUIPMENT SUBJECT INDEX

RADAR EQUIPMENTAnalysis of F-16 radar discrepancies

[AD-A124749] p 476 N83-25948RADAR SCANNING

Scanning strategies (or next generation weather radarsA study based on lifetimes of convective atmosphericphenomena hazardous to aviation[FAA-RD-8269] p 476 N83-25929

RADIATION HAZARDSLaser safety of air bathymetry

[FOA-C-30292-E1] p 478 N83-27210RADIO ANTENNAS

A rapid-tuning high-power pod-mounted VHP antennasystem p 430 A83-35088

RADIO FREQUENCY SHIELDINGComposite material aircraft electromagnetic properties


RADIO RECEIVERSSH-3 helicopter/Global Positioning System integration

analysis[AD-A125005] p 432 N83-25691

RADIO WAVESRF radiation from lightning correlated with aircraft

measurements during storm hazards-82(NASA-TM-85007) p 479 N83-27537

RADOMESWind tunnel test of a C-18 aircraft modified with the

advanced range instrumentation aircraft radome(AD-A124771 ] p 425 N83-25671

RAMAN SPECTROSCOPYCARS temperature and species measurements in

augmented jet engine exhausts - Coherent Anti-StokesRaman Spectroscopy[AIAA PAPER 83-1294] p 455 A83-36328

RAMJET ENGINESApplications of computational techniques in the design

of ramjet engines p 418 A83-35828Response of a supersonic inlet to downstream


RAMJET MISSILESNew transformations of S4 Modane hypersonic wind

tunnel for ramjet missiles tests| ONER A, TP NO 1983-24] p 464 A83-36433


REAL TIME OPERATIONSinusoidal integration for simulation of second-order




Real time simulation of mission environments foravionics systems integration[AIAA PAPER 83-1097] p 463 A83-36217

Design of a real-time CGSI system[AIAA PAPER 83 1101) p 474 A83-36221


RECIRCULATIVE FLUID FLOWThe effect of fuel atomization on soot-free combustion

in a prevaporiztng combustor p 446 A83-35812RECORDING INSTRUMENTS


RECTANGULAR WINGSCalculation of subsonic flow past rectangular wings and



Some recent applications of XTRAN3S[NASA-TM-85641] p 426 N83-26815

REGENERATIVE COOLINGPreliminary investigation on the performance of


REGULATORSInteractive fine-tuning of linear-quadratic governers by


RELIABILITY ANALYSISA dynamic model of turbojet in starting at high altitude

p447 A83-35846REMOTE CONSOLES

The remote link unit A demonstration of operationalperformance Part 3 Design manual, volume 1[AD-A124621] p 476 N83-25934




REMOTELY PILOTED VEHICLESA true air speed sensor for miniature unmanned

aircraft p 444 A83-36613RESEARCH AIRCRAFT

On the propulsion system of the NAL quiet STOLresearch aircraft p 446 A83-35831


The F-16 - A technology demonstrator, a prototype, anda flight demonstrator[AIAA PAPER 83-1063] p 438 A83-36467


The Northrop Flying Wing prototypes[AIAA PAPER 83-1047] p416 A83-36471


RESEARCH AND DEVELOPMENTFrom Voyageur on - The exploitation of an opportunity

to develop a Canadian air cushion vehicle industry —developing Canadian Air Cushion Vehicle Industry

p 485 A83-35052Developments in air cushion vehicle spray

suppression p 486 A83-35056Skirts - Time for a new look' p 486 A83-35058The Transportation Development Centre contribution to

air cushion technology p 486 A83-35059Design and development of a small gasturbme engine

Results today - A basis lor design criteria of a nextgeneration p 446 A83-35829

Design and development of a nozzle extendible exitcone[AIAA PAPER 83-1410] p 467 A83-36399




Air Force technical objective document FY 1984[AD-A123961] p 487 N83-26783


RESEARCH FACILITIESThe man-vehicle systems research facility - A new NASA


RESEARCH PROJECTSAn over view of UTIAS research on the dynamic stability

of air cushion vehicles p 484 A83-34853RESIDUAL STRESS


RESONANT FREQUENCIESResonance tests on the tail of a CT4 aircraft

[AD A124566] p 441 N83-25703RESONANT VIBRATION


p 449 A83-35881RETROFITTING


REVERSED FLOWApplication of 3D aerodynamic/combustion model to


REYNOLDS NUMBERCondensation studies in cryogenic nitrogen

expansions p 465 N83-25720Problems involved by the instrumentation and the

conception of cryogenic tests p 465 N83-25725REYNOLDS STRESS


RIGID ROTORSCoupled flap-lag torsional dynamics of hmgeless rotor

blades in forward flight p 433 A83-33506Coupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 435 A83-35948ROCKET ENGINES

International Symposium on Air Breathing Engines, 6th,Pans, France, June 6-10, 1983, Symposium Papers

p 445 A83-35801

ROLLExperimental testing of flying qualities theories

(AD-A124699] p 440 N83-25697ROLLER BEARINGS


ROTARY STABILITYF-14 rotary balance tests for an angle-of-attack range

of 0 deg to 90 deg[AD-A124468] p 441 N83-25700

ROTARY WING AIRCRAFTResearch and analysis of head-directed area of-mterest


ROTARY WINGSEvaluation of the effect of voids in composite mam rotor

blades p 472 A83-33507A tubular braided composite mam rotor blade spar

p435 A83-35949Evaluation of the effect of voids in composite mam rotor

blades p 435 A83-35950The super stallion — CH-53E helicopter design

features p 435 A83-36075Spectral decontamination of a real-time helicopter

simulation(AIAA PAPER 83-1087) p 436 A83-36211



Verification testing of an AH-1S Wire Strike ProtectionSystem (WSPS)[AD-A123188] p 429 N83-25684

Experimental study of mam rotor/tail rotor/airframeinteractions in hover Volume 1 Text and figures[NASA-CR-166485] p 427 N83-26820

Simulation program of rotary wings[FOA-C-30308-E1] p 443 N83-26836

ROTATING DISKSThe influence of defects on the operational strength

of disks and wheels in engines p 472 A83-33964ROTATING STALLS

Flow measurements within rotating stall cells in singleand multistage axial-flow compressors

p419 A83-35873Flow in rotating stall cells of a low speed axial flow

compressor p419 A83-35874ROTOR AERODYNAMICS


Helicopter rotor loads using matched asymptoticexpansions User's manual[NASA-CR-166093J p 423 N83-25659


Correlation and evaluation of inplane stabilitycharacteristics for an advanced bearmgless mam rotor[NASACR-166448] p 440 N83-25695

ROTOR BLADESExcitation and vibration of flexible bladed disks under

operating and simulated operation conditionsp 449 A83-35881


Full-scale measurements of blade vortex interactionnoise p 435 A83-35947


ROTOR BLADES (TURBOMACHINERY)Effect of entry boundary layer thickness on secondary




ROTORSDamping seal for turbomachmery

[NASA-CASE-MFS-25842-1] p 477 N83-26080ROUTES

A theoretical framework for analysis of lateral positionerrors in VOR jet-route systems p 431 A83-35273


RUBIDIUMPhase 2A bench model development tactical rubidium


A-20

SUBJECTINDEX STATIC PRESSURE

RUNWAYSU S sets own standards for airport lighting

p 463 A83 35625Runway surface condition sensor specification guide

[AC-150/5220-13A) p 465 N83 25728

SAFETYForeign Technology Alert - Bibliography Transportation

safety[PB83-101659] p430 N83 25686

SANDSEffect of sand erosion on Ihe performance deterioration

of a single stage axial flow compressorp448 A83-35854

SCALE MODELSDevelopment of a turbojet engine simulator for scale

model wind tunnel testing of multi-mission aircraftp447 A83-35848

Propulsion system simulation technique (or scaled windtunnel model testing p 463 A83-35850

STOL wind tunnel test results for a tacticalsupercruiser[AIAA PAPER 83-1224] p 420 A83-36291

Performance capability of a Compact MultimtssionAircraft Propulsion Simulator[AIAA PAPER 83-1358] p 464 A83-36356


SCREEN EFFECTOptimum wire screens for control of turbulence in wind

tunnels p417 A83-33772SEALS (STOPPERS)

Experimental investigation on the role of flexbars andmetallic end seals in squeeze film dampers — of gas turbineengines p 473 A83-35862

Fluoroelastomers — materials for hostile fluidenvironments p 469 A83-36066

Design analysis of a self-acting spiral-groove ring seal1or counter-rotating shafts[NASA-TP-2142] p 458 N83-25712

Damping seal for turbomachmery[NASA-CASE-MFS-25842-1 ] p 477 N83-26080

SEAT BELTSACES II negative Gz restraint investigation

[AD-A124713) p 430 N83-25685SECONDARY FLOW

A contribution to the calculation of secondary flows inan axial flow compressor p419 A83-35852

Effect of entry boundary layer thickness on secondaryflows in an annular cascade of turbine nozzle and rotorblades p419 A83-35868

SECURITYSandia Helicopter Acoustic Detector (SHAD)

[DE82-018925] p 483 N83-27803SELF INDUCED VIBRATION

Forced and self-excited vibrations of gas turbineassemblies with perfect and perturbed symmetry

p 458 A83-36791SENSITIVITY

Survivabihty of interdiction aircraft Sensitivity to terrainfollowing, command altitude, velocity and electroniccounter measures[AD-A124870] p 443 N83-26833

SENSORSPerformance capabilities of photographic flight


SEPARATED FLOWSeparated flows on a concave conical wing

p 418 A83-35707Dynamic distortion in a short s-shaped subsonic diffuser

with flow separation — Lewis 8 by 6 foot Supersonic WindTunnel[NASA-TM-84312] p 459 N83-26838

SERVICE LIFEMaterial, structural component, service life — of aircraft

construction materials p 468 A83-33953Component life reduction due to use of AVGAS in gas

turbine engines p 449 A83-35869Life prediction for turbine engine components

p474 A83-36174SHEAR STRESS

Nonlinear supersonic flutter of panels considering sheardeformation and rotary inertia p 473 A83-34315

Experimental studies of the separating confluentboundary layer Volume 1 Summary[NASA-CR-3655] p 427 N83-26822

SHOCK TUBESNOVA-2S correlation with KC-135A fuselage shock lube

test results[AD-A124013] p466 N83-25732

SHORT HAUL AIRCRAFTApplications of advanced upper surface blowing


SAAB-Fairchild 340 - Transatlantic frontrunnerp 434 A83-35623

Advanced turboprop and dual cycle engine performancebenefits and installation options on a Mach 0 7 shorthaultransport aircraft[AIAA PAPER 83-1212] p 452 A83 36284

SHORT TAKEOFF AIRCRAFTOn the propulsion system of the NAL quiet STOL

research aircraft p 446 A83 35831Entramment and mixing in thrust augmenting ejectors

[AIAA PAPER 83-0172] p 419 A83-36046STOL wind tunnel test results for a tactical

supercruiser[AIAA PAPER 83-1224] p 420 A83-36291

A high speed wind tunnel test evaluation of STOLdedicated advanced exhaust nozzle concepts[AIAA PAPER 83-1225) p 421 A83 36292

Thrust reverser exhaust plume Remgestion tests for aSTOL fighter model[AIAA PAPER 83-1229) p 452 A83-36293

Definition of vectored nonaxisymmetnc nozzle plumes- - for aircraft thrust vector control[AIAA PAPER 83-1290] p 423 A83-36924



SIGNAL PROCESSINGComparative analysis of a phase and an amplitude


Numerical treatment of Doppler radar signals -- airportradar, video data[ENST-E-82014] p 478 N83-27114

SIGNAL TO NOISE RATIOSComparative analysis of a phase and an amplitude



SINE WAVESSinusoidal integration for simulation of second order


Computation of incompressible potential flow over anairtoil using a high order aerodynamic panel method basedon circular arc panels[AD-A124896] p 428 N83-26825

SKID LANDINGSSome applications of ultrasonic methods for the quality

control of nonmetallic objects p 475 A83-36794SKIRTS

Skirts - Time for a new look' p 486 A83-35058Net-skirt addition to a parachute canopy to prevent

inversion p 428 A83-36911SMOKE


SOFTWARE TOOLSAn interactive bombing mission simulation with computer

graphics interface[AD-A124661] p481 N83-26637

SOLID LUBRICANTSFeasibility of dry lubrication for timited-duty gas turbine

engines[AIAA PAPER 83-1130] p 475 A83-36405

SOUND FIELDSInvestigation of the coupling of unsteady lift to low order


SOUND PRESSURECross spectra between temperature and pressure in a


SOUND PROPAGATIONEdge tones m high-speed flows and their application

to multiple-jet mixing p 482 A83-36077SOUND TRANSDUCERS

Sandia Helicopter Acoustic Detector (SHAD)[DE82-018925I p 483 N83 27803

SPACE SHUTTLE ORBITERSTransient heat-transfer measurement technique in wind


SPACE STATIONSSpace-station crew-safety requirements

p 467 A83 36408SPACECRAFT CONSTRUCTION MATERIALS

Air Force technical objective document FY 1984[AD-A123961] p 487 N83 26783

SPACECRAFT DESIGNAerospace technology demonstrators/research and

operational options[AIAA PAPER 83-1054] p 438 A83 36465

SPACECRAFT MANEUVERSA small parameter method in problems of maneuvering


SPACECREWSSpace-station crew-safety requirements

p 467 A83-36408SPECIFIC HEAT


SPEED INDICATORSA true air speed sensor for miniature unmanned

aircraft p 444 A83-36613SPIN DYNAMICS

F-14 rotary balance tests tor an angle-ot-attack rangeof 0 deg to 90 deg[AD-A124468] p 441 N83 25700

SPLINE FUNCTIONSSurfaces in computer aided geometric design,


SQUARE WAVESA note on adaptive wind tunnels with imperfect control

p466 N83-26792SQUEEZE FILMS

Experimental investigation on the role of flexbars andmetallic end seals in squeeze film dampers — of gas turbineengines p 473 A83-35862

STABILITYFlutter prediction in forward swept wings by assumed

modes and strip theory[AD-A124715] p 461 N83-25719

STABILITY DERIVATIVESApplication of maximum likelihood estimation to the


STABILIZERS (FLUID DYNAMICS)Advanced manufacturing development of a composite


Investigation of an improved finite element model for arepaired T-38 horizontal stabilizer flutter analysis usingNASTRAN[AD-A124741) p461 N83-25717

Structural model tuning via vector optimization[AD-A124791) p477 N83-26103

STACKSAn investigation of the effectiveness of smoke

suppressant fuel additives for turbojet applications[AO-A125025] p471 N83-27034

STAGNATION FLOWPrediction of stagnation flow heat transfer on


STAGNATION POINTCalculation of boundary layers near the stagnation point


STAGNATION TEMPERATURECondensation studies in cryogenic nitrogen

expansions p 465 N83-25720STALLING


STANDARDSU S sets own standards for airport lighting

p 463 A83-35625Proposed MIL standard and handbook Flying qualities

of air vehicles Volume 2 Proposed MIL handbook[AD-A123726] p 441 N83-25704

STANDING WAVESInvestigation of the coupling of unsteady lift to low order


STATIC PRESSUREThe swirl m an S-duct of typical air intake proportions

p418 A83-35620Force and pressure measurements on a research model

with a low-, mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p 425 N83-25676


A-21

STATISTICAL ANALYSIS SUBJECT INDEX

STATISTICAL ANALYSISStatistical experimental designs in computer aided

optimal aircraft design p 442 N83-26812Statistical review of counting accelerometer data for

Navy and Marine fleet aircraftIAD-A124966] p 443 N83-26834

STATOR BLADESEffects of compressor hub treatment on stator stall

margin and performance[AIAA PAPER 83-1352) p 475 A83-36354

STATORSDamping seal for turbomachmery

| NASA CASE-MFS 25842-1 ] p 477 N83-26080STEADY FLOW

Flutter prediction in forward-swept wings by assumedmodes and strip theoryIAD-A124715] p461 N83-25719

STEPSSemi implicit calculation method of the flow field in a


STOCHASTIC PROCESSESInvestigation of a third order baro-damped verticle

channel of INSIAD-A124882] p 432 N83-26828

STORMSScanning strategies for next generation weather radars

A study based on lifetimes of convective atmosphericphenomena hazardous to aviation(FAA-RD-82-69] p 476 N83-25929

STRAIN GAGESApplication of thin film strain gages and thermocouples

for measurement on aircraft engine parts| AIAA PAPER 83-1292] p 444 A83-36326

STRESS ANALYSISCoupled flap-lag torsional dynamics of hmgeless rotor

blades in forward flight p 433 A83-33506Stress analysis of critical areas of low-pressure

compressor-disc assembly of a developmentalaero-engme p 449 A83-35880

Flight tests of tow wire forces while flying a racetrackpattern p 439 A83-36919

Static aeroelastic analysis of flexible wings viaNASTRAN, part 1IAD-A124662] p 477 N83-26099

STRESS CONCENTRATIONThe use of a structural model for determining the

adaptability curve for turbine disks in stress concentrationzones p 445 A83-35039

STRESS MEASUREMENTInvestigation methods on residual stresses in aero

engines components p 449 A83-35879STRUCTURAL ANALYSIS

Resonance tests on the tail of a CT4 aircraft[AD-A124566J p 441 N83-25703

Analysis of progressive collapse of complex structures[AD-A125266J p 478 N83-27260

STRUCTURAL DESIGNOptimization for structures of discrete-size elements

p472 A83-34311Progress in propulsion system/airframe structural


Development trends in engine durability — for USAFaircraft gas turbines|AIAA PAPER 83-1297] p 455 A83-36329

STRUCTURAL DESIGN CRITERIAComposite material aircraft electromagnetic properties


STRUCTURAL FAILUREContainment of turbine engine fan blades

p 449 A83-35871STRUCTURAL MEMBERS

Matenals and modelling technology for cryogenicenvironment p 465 N83-25723

STRUCTURAL RELIABILITYAdvanced manufactunng development of a composite


STRUCTURAL VIBRATIONAircraft equipment random vibration test criteria based



SUBSONIC FLOWThe aerodynamics of hyposonic velocities (On flows with

low Mach numbers) p 417 A83-35535Calculation of subsonic flow past rectangular wings and


The swirl in an S-duct of typical air intake proportionsP418 A83-35620


p474 A83-36085Method for calculating effects of a propfan on aircraft

aerodynamics at subsonic speeds[AIAA PAPER 83-1216] p 420 A83-36287


SUBSONIC SPEEDModel aerodynamic test results for a refined actuated

inlet elector nozzle at simulated takeoff and cruiseconditions[NASA-CR-168051] p 426 N83-26816

SUCTIONExperimental investigation of the effects of wall suction


SUPERCRITICAL WINGSSome recent applications of XTRAN3S

[NASA-TM-85641] p 426 N83-26815SUPERSONIC AIRCRAFT


SUPERSONIC CRUISE AIRCRAFT RESEARCHInlet, engine, airframe controls integration development

for supercruismg aircraft p 447 A83-35842SUPERSONIC DIFFUSERS


SUPERSONIC FLIGHTEffects of varying podded nacelle-nozzle installations

on transonic aeropropulsrve characteristics of a supersonicfighter aircraft[NASA-TP-2120) p 427 N83-26821

SUPERSONIC FLOWApplications of computational techniques in the design

of ramiet engines p418 A83-35828SUPERSONIC FLUTTER

Nonlinear supersonic flutter of panels considering sheardeformation and rotary inertia p 473 A83-34315

SUPERSONIC INLETSInlet, engine, airframe controls integration development

for supercruismg aircraft p 447 A83-35842Response of a supersonic inlet to downstream



SUPERSONIC NOZZLESEffects of varying podded nacelle-nozzle installations

on transonic aeropropulsive characteristics of a supersonicfighter aircraft[NASA-TP-2120] p 427 N83-26821

SUPERSONIC SPEEDSModel aerodynamic test results for a refined actuated

inlet elector nozzle at simulated takeoff and cruiseconditions[NASA-CR-168051] p 426 N83-26816

SUPERSONIC TRANSPORTSTechnology status for an advanced supersonic


Elector nozzle test results at simulated flight conditionsfor an advanced supersonic transport propulsion system[AIAA PAPER 83-1287] p 454 A83-36323

SUPPORT INTERFERENCEAn algorithm of flight simulation on a dynamic stand of

support type p 462 A83-34429SUPPORT SYSTEMS

Operational deployment of the air cushion vehiclep485 A83-34864

LACV-30 supportablllty p 486 A83-35062SUPPORTS


SURFACE EFFECT SHIPSFrom Voyageur on - The exploitation of an opportunity

to develop a Canadian air cushion vehicle industry —developing Canadian Air Cushion Vehicle Industry

p485 A83-35052A new class ACV - Tanker-freighter

p485 A83-35053A design synthesis model for ACV/SES lift systems

p 486 A83-35057SURFACE GEOMETRY

Surfaces in computer aided geometric designProceedings of the Conference, Oberwolfach, WestGermany, April 25-30, 1982 p 480 A83-33613

SURFACE PROPERTIESRunway surface condition sensor specification guide

[AC-150/5220-13A] p 465 N83-25728SURFACE ROUGHNESS


SURFACE TEMPERATURETemperature response of a model to set-point changes

and conditioning in ETW p 465 N83-25721SWEPT FORWARD WINGS




SWEPT WINGSProgress toward the analysis of complex propulsion


SWIRLINGThe swirl in an S-duct of typical air intake proportions

p 418 A83-35620The performance of an annular vane swirler — to aid

in modeling gas turbine combustor llowfields and swirlingconfined flow turbulence[AIAA PAPER 83-1326] p 455 A83-36340

SYSTEM IDENTIFICATIONApplication of system identification flight analysis


Transient heat-transfer measurement technique in windtunnel and data analysis technique using systemidentification theory[AD-A124663] p 424 N83-25669

SYSTEMS ANALYSISSimulator performance definition by cue synchronization

analysis(AIAA PAPER 83-1092] p 463 A83-36216

An interactive bombing mission simulation with computergraphics interface[AD-A124661] p481 N83-26637


SYSTEMS ENGINEERINGThe man-vehicle systems research facility - A new NASA


Design of a real-time CGSI system[AIAA PAPER 83-1101 ] p 474 A83-36221


Advanced propulsion controls - A total system viewp 457 A83-36612

SYSTEMS INTEGRATIONInlet, engine, airframe controls integration development

for supercruismg aircraft p 447 A83-35842Flight/propulsion control system integration

[AIAA PAPER 83-1238] p 453 A83-36301Design for testing of a low altitude night-in-weather

attack system[AIAA PAPER 83-1061 ] p 432 A83-36470



SYSTEMS MANAGEMENTFlight management concepts development for fuel

conservation p 447 A83-35843SYSTEMS SIMULATION


p 449 A83-35881SYSTEMS STABILITY


p460 A83-33900

T-56 ENGINEEffect of fuel composition on Navy aircraft engine hot

section components[AIAA PAPER 83 1147] p 450 A83-36244

Aspects of the T56 power section usage/operatingcosts[AIAA PAPER 83-1408] p 457 A83-36397

A-22

SUBJECT INDEX TRACKING PROBLEM

TAIL ASSEMBLIESEmpennage/afterbody integration for single and

twin-engine fighter aircraft[AIAA PAPER 83-1126] p 420 A83-36235

Effect of empennage location on twin-engineafterbody-nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2 -- wind tunnel tests[NASA-TP-2116] p424 N83-25666

Force and pressure measurements on a research modelwith a low-, mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p425 N83-25676

TAILLESS AIRCRAFTThe Northrop Flying Wing prototypes

[AIAA PAPER 83-1047] p416 A83-36471TAKEOFF

Model aerodynamic test results tor a refined actuatedinlet ejector nozzle at simulated takeoff and cruiseconditions[NASA-CR-168051] p 426 N83-26816

TARGETSFlight tests of tow wire forces while flying a racetrack

pattern p 439 A83-36919TAXIING

Guidance control systems for aircraft on airportsurfaces[AIAA PAPER 83-1579] p 429 A83-36953

TECHNOLOGICAL FORECASTINGA survey of trends in modern turbine technology

[AIAA PAPER 83-1174] p 451 A83-36260The future of the manned aircraft p 416 A83-36960

TECHNOLOGY ASSESSMENTTechnology status for an advanced supersonic


Applications of advanced upper surface blowingpropulsive-lift technology[SAE PAPER 820956] p 433 A83-33628

Prop-fan powered aircraft - An overview[SAE PAPER 820957] p 434 A83-33629

Flight Simulation Technologies Conference, NiagaraFalls, NY, June 13-15, 1983, Collection of TechnicalPapers p415 A83-36203

Advanced propfan engine characteristics andtechnology needs[AIAA PAPER 83-1155] p 450 A83-36250

Configuration selection and technology transition in 5000SHP class engines[AIAA PAPER 83-1411 ] p 457 A83-36400

1983 LTA technology assessment[AIAA PAPER 83-1617] p 437 A83-36406

Aircraft production technology (2nd revised and enlargededition) — Russian textbook p415 A83-36443


The application of low-cost demonstrators foradvancead fighter technology evaluation[AIAA PAPER 83-1052] p 438 ' A83-36462





TEMPERATUREClimatic laboratory survey Hughes YAH-64 helicopter

[AD-A124670] p 440 N83-25698TEMPERATURE EFFECTS

A study of the response of a turbojet engine to the inlettemperature transients p 448 A83-35849

TEMPERATURE MEASUREMENTTemperature and composition measurements in a



CARS temperature and species measurements inaugmented |et engine exhausts — Coherent Anti-StokesRaman Spectroscopy[AIAA PAPER 83-1294] p 455 A83-36328

Method of studying the operating temperature of gasturbines — aeroengines[PNR-90159] p460 N83-26842

TENSILE STRENGTHEvaluation of low-cost aluminum composites for aircraft


TERRAINSurvivability of interdiction aircraft Sensitivity to terrain


TERRAIN FOLLOWING AIRCRAFTSurvivability of interdiction aircraft Sensitivity to terrain

following, command altitude, velocity and electroniccounter measures[AD-A124870] p443 N83-26833

TEST FACILITIESCanadian forces tracker aircraft full-scale fatigue test



NASA low speed centrifugal compressor forfundamental research[NASA-TM-83398) p 424 N83-25662

Analysis and specification of slant wind shear[AD-A125883] p 479 N83-26367

A compact inflow control device for simulating flight fannoise[NASATM-83349] p 482 N83-26643

TEST PILOTSIndoctrination of Navy test pilots to vectored thrust flight

in the X-22A in-flight simulator[AIAA PAPER 83-1076] p 436 A83-36205

In flight simulation at the U S Air Force and Naval TestPilot Schools[AIAA PAPER 83-1078] p 436 AB3-36206

TEST STANDSDetermination of the sensitivity of U S Air Force aircraft


THERMAL ABSORPTIONConcepts for increased power and enhanced fuel


THERMAL CYCLING TESTSThermal cycling in compact plate-fin heat exchangers

— in aircraft gas turbines p 445 A83-34253THERMAL NOISE

Comparative analysis of a phase and an amplitudeprocessor for amplitude monopulse systems

P431 A83-35192THERMAL PROTECTION

Transient heat transfer measurement technique in windtunnel and data analysis technique using systemidentification theory[AD-A124663] p 424 N83-25669

Air Force technical objective document FY 1984[AD-A123961] p487 N83-26783

THERMAL STABILITYThermal stability of alternative aircraft fuels

[AIAA PAPER 83-1143] p 470 A83-36243THERMAL STRESSES


THERMOCOUPLESApplication of thin film strain gages and thermocouples

for measurement on aircraft engine parts[AIAA PAPER 83-1292] p 444 A83-36326

Early expenence in using the Cryogenic Test Facilityat RAE Bedford, England p 465 N83-25726

THERMOOYNAMIC CYCLESCriteria tor optimizing starting cycles for high


Cruise missile propulsion versus commercial airlinerpropulsion - Different challenges can produce similarengine cycles[AIAA PAPER 83-1176] p 451 A83-36261

THERMOELECTRICITYNumencal simulation of electrothermal de-icing


THIN FILMSApplication of thin film strain gages and thermocouples


THIN WINGSImproved numencal method for unsteady lifting surfaces

in incompressible flow p 422 A83-36917THREE DIMENSIONAL BOUNDARY LAYER

Evaluation of a surface panel method coupled withseveral boundary layer analyses[AIAA PAPER 83-0011 ] p 474 A83-36039

THREE DIMENSIONAL FLOWAerodynamic optimization theory of A 3-D axial-flow

rotor-blading via optimal control p418 A83-35839Flow measurements within rotating stall cells in single

and multistage axial-flow compressorsp419 A83-35873

Numencal calculations of time dependentthree-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-1171] p 420 A83-36258

Progress toward the analysis of complex propulsioninstallation flow phenomenon(AIAA PAPER 83-1367 ] p 421 A83 36363

Three-dimensional compressible viscous analysis ofmixer nozzles[AIAA PAPER 83-1401 ] p 422 A83 36391

Some recent applications of XTRAN3S[NASA-TM-85641] p 426 NB3-26815

THRUST AUGMENTATIONPreliminary investigation on the performance of


Entrainment and mixing in thrust augmenting ejectors[AIAA PAPER 83-0172] p 419 A83-36046

THRUST REVERSALThrust reverser exhaust plume Remgestion tests for a


Results of tests of a rectangular vectoring/reversingnozzle on an F100 engine(AIAA PAPER 83-1285] p 454 A83-36322

Thrust performance of a variable-geometry, divergentexhaust nozzle on a turbojet engine at altitude(NASA-TP-2171] p459 N83-26839

THRUST VECTOR CONTROLVectored thrust afterbody nozzles for future combat

aircraft p 448 A83-35859Indoctrination of Navy test pilots to vectored thrust flight

in the X-22A m-fhght simulatorI AIAA PAPER 83-1076] p 436 A83-36205

STOL wind tunnel test results for a tacticalsupercruiser[AIAA PAPER 83-1224) p 420 A83-36291

A high speed wind tunnel test evaluation of STOLdedicated advanced exhaust nozzle concepts(AIAA PAPER 83-1225] p 421 A83-36292

Results of tests of a rectangular vectoring/reversingnozzle on an F100 engine[AIAA PAPER 83-1285) p 454 A83-36322

Definition of vectored nonaxisymmetnc nozzle plumes— for aircraft thrust vector control(AIAA PAPER 83-1290] p 423 A83-36924


THUNDERSTORMSRF radiation from lightning correlated with aircraft

measurements during storm hazards-82[NASA-TM-85007] p 479 N83-27537

TIME DEPENDENCENumerical calculations of time' dependent

three-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-1171 ] p 420 A83-36258

TIME DIVISION MULTIPLEXINGThe remote link unit A demonstration of operational

performance, part 1[AD-A124619] p 476 N83-25939

TIME FUNCTIONSMethod of studying the operating temperature of gas


TIME LAGCompensation for time delay in flight simulator

visual-display systems[AIAA PAPER 83-1080] p 464 A83-36222

TIME OPTIMAL CONTROLMicroprocessor-based optimal controllers for a

helicopter turret control system p 434 A83-35138TITANIUM

Microeconomic models for process developmentp 472 A83-33650

TORSIONAL STRESSCoupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 433 A83-33506Coupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 435 A83-35948TORSIONAL VIBRATION

Vibrational diagnostics of gas-turbine bladesp 473 A83-35040

TOWED BODIESImpact damping and airplane towing


pattern p 439 A83-36919TRACKING (POSITION)

Lateral flying qualities of highly augmented fighteraircraft, volume 1[ AD-A118070 ] p 443 N83-26835

TRACKING PROBLEMOld problem/new solutions - Motion cuing algonthms


A-23

TRAINING ANALYSIS SUBJECT INDEX

TRAINING ANALYSISGreater benefits to be gained from DoD flight

simulatorsIAD-A123713] p 466 N83-25731

TRAINING EVALUATIONSimulator design features for carrier landing Part 2

In-simulator transfer of training[AD-A124024] p466 N83-25733

TRAINING SIMULATORSGreater benefits to be gained from DoD flight

simulatorsIAD-A123713] p 466 N83-25731

TRANSFER OF TRAININGSimulator design features for carrier landing Part 2

In-simulator transfer of trainingIAD-A124024] P466 N83-25733

TRANSIENT HEATINGTransient heat flow along um-directional fibers in


TRANSIENT LOADSImpact damping and airplane towing

p 428 A83-33625TRANSIENT RESPONSE

The transient performance of turboiet engines and axialcompressors p 447 A83-35847

TRANSMISSIONS (MACHINE ELEMENTS)In-flight computation of helicopter transmission fatigue

life expenditure p 439 A83-36921TRANSONIC COMPRESSORS

Experimental study of a high-through-flow transonic axialcompressor stage p 419 A83-35853

TRANSONIC FLIGHTModel aerodynamic test results for a refined actuated

inlet ejector nozzle at simulated takeoff and cruiseconditions(NASA-CR-168051] p 426 N83-26816

TRANSONIC FLOWFinite differecnce calcultion of an inviscid transonic flow

over oscillating airfoils[AD-A123982] p 426 N83-25677


TRANSONIC WIND TUNNELSPrograms for the transonic wind tunnel data processing

installation Part 10 Six component measurementsupdated(AD-A122248J p 427 N83-26824

TRANSPORT AIRCRAFTThe Dash 8 development'program

p 433 A83-33546Application of maximum likelihood estimation to the



PAN AIR applications to aero-propulsion integration[AIAA PAPER 83 1368] p 421 A83-36364

The Ka 26 helicopter — Russian bookp 437 A83-36448

TRANSPORTATIONForeign Technology Alert - Bibliography Transportation

safety[PB83-101659] p430 N83-25686

TRIANGULATIONSurfaces in computer aided geometric design.


TURBINE BLADESProfile losses during the release of air onto the surface

of nozzle vanes p 418 A83-35590Aerodynamic optimization theory of A 3-D axial-flow

rotor-bladmg via optimal control p 418 A83-35839Containment of turbine engine fan blades

p 449 A83-35871Design of dry-fnction dampers for turbine blades

p450 A83-35883Prediction of stagnation flow heat transfer on




TURBINE ENGINESStatistical study of TBO and estimation of acceleration


p 448 A83-35858Life prediction tor turbine engine components

p474 A8336174Deterioration trending enhances |et engine hardware



Accelerated simulated mission endurance test of aturboshaft engine for military attack helicopterapplicationI AIAA PAPER 83-1359] p 455 A83-36357

TURBINE EXHAUST NOZZLESEffect of entry boundary layer thickness on secondary


TURBINE WHEELSResidual life prediction for jet engine rotor disks at

elevated temperature p 472 A83-33974The use of a structural model for determining the

adaptability curve for turbine disks in stress concentrationzones p 445 A83-35039

A contribution to airworthiness certification of gas turbinedisks p 449 A83-35872

Stress analysis of critical areas of low-pressurecompressor disc assembly of a developmentalaero-engine p 449 A83-35880





TURBOCOMPRESSORSPreliminary investigation on the performance of




A contribution to the calculation of secondary flows inan axial flow compressor p 419 A83-35852 '

Expenmental study of a high-through-flow transonic axialcompressor stage p 419 A83-35853

Effect of sand erosion on the performance deteriorationof a single stage axial flow compressor

p 448 A83-35854Effect of humidity on jet engine axial-flow compressor

performance p 448 A83-35856Flow measurements within rotating stall celts in single


Flow in rotating stall cells of a low speed axial flowcompressor p 419 A83-35874

Design and performance of a low aspect ratio, high tipspeed multi-stage compressor[AIAA PAPER 83-1161] p 451 A83-36253

Maximum loading capability of axial flow compressors[AIAA PAPER 83-1163) p 451 A83-36254




Finite element program for calculating flows inturbomachines with results for NASA task-1 compressor[AD-A124987] p 460 N83-26841

TURBOFAN ENGINESAcoustic modal analysis of a full-scale annular


Further study on the prediction of liquid fuel spray captureby v-gutter downstream of a plain orifice injector underuniform cross air flow p 473 A83-35810

Expenmental research of the mechanism of flamestabilization in two phase mixture p 469 A83-35822

Preliminary investigation on the performance ofregenerative turbofan with inter-cooled compressor andits influence to aircraft p 446 A83-35830



Methanol combustion in a CF6I-80A engine combustorCA(AA PAPER 83-1138] p 469 A83-36241

The aerodynamic design and performance of theGeneral Electric/NASA EEE fan — Energy EfficientEngineI AIAA PAPER 83-1160] p 451 A83-36252

Cruise missile propulsion versus commercial airlinerpropulsion - Different challenges can produce similarengine cycles[AIAA PAPER 83-1176] p 451 A83-36261




Design analysts of a self-acting spiral-groove ring sealfor counter-rotating shafts[NASA-TP-2142] p 458 N83-25712


A compact inflow control device for simulating flight fannoise[NASA-TM-83349] p 482 N83-26643

Advances in ejector technology A tribute to Hans vonChain's vision p 477 N83-26805

TURBOJET ENGINESDesign and development of a small gasturbine engine



p446 A83-35832A dynamic model of turbojet in starting at high altitude

p 447 A83-35846The transient performance of turbojet engines and axial

compressors p 447 A83-35847Development of a turbojet engine simulator for scale



Ground simulation of engine operation at altitudep463 A83-35863

Generalization of the air-jet propulsion systems, the 'N'flow turbo-jet engine[AD-A123932] p 459 N83-25715



TURBOMACHINE BLADESVibrational diagnostics of gas-turbine blades

p 473 A83-35040High temperature erosion study of INCO 600 metal

p 468 A83-35247TURBOMACHINERY



TURBOPROP AIRCRAFTThe Dash 8 development program

p 433 A83 33546Aerodynamic design of preplan powered transports

[AIAA PAPER 83-1213] p 437 A83-36285TURBOPROP ENGINES

AR 318 - Italy's low-cost GA turbopropp445 A83-35675


TURBULENT FLOWOptimum wire screens for control of turbulence in wind

tunnels p417 A83-33772Numerical computation of turbulent flow around the

spinner of a turbofan engine p 418 A83 35838Aircraft equipment random vibration test criteria based


TURBULENT MIXINGEntramment and mixing in thrust augmenting ejectors

[AIAA PAPER 83-0172] p 419 A83 36046TWO DIMENSIONAL BOUNDARY LAYER

Evaluation of a surface panel method coupled withseveral boundary layer analyses[AIAA PAPER 83-0011] p 474 A83-36039

Application of a finite difference method to the transonicairfoil problem[AD-A124720] p 425 N83-25674

TWO DIMENSIONAL FLOWHigh angle-of-attack cascade measurements and

analysis p 419 A83-35875

A-24

SUBJECT INDEX WIND TUNNEL APPARATUS

A note on adaptive wind tunnels with imperfect controlP466 N83-26792

Feasibility study of three dimensional holographicmterferometry for aerodynamics[NASA-CR-166483] p 483 N83-27845

TWO PHASE FLOWExperimental research of the mechanism of flame

stabilization in two phase mixture p 469 A83-35822

uUH-1 HELICOPTER

Full scale measurements of blade-vortex interactionnoise p 482 A83-33505

Full-scale measurements of blade-vortex interactionnoise p435 A83-35947

ULTRALIGHT AIRCRAFTA complete introduction to the revolutionary new way

to fly ultralights — Book p415 A83-33622ULTRASONIC FLAW DETECTION


ULTRASONIC WELDINGUltrasonic weld bonding of helicopter primary


UNITED KINGDOMUnited Kingdom military engine usage, condition and

maintenance systems experience[AIAA PAPER 83-1239] p 453 A83-36302

UNSTEADY FLOWFlow measurements within rotating stall cells in single


Integro-differential equations of the dynamics of elasticsystems m nonstationary flows — flight vehicle dynamicsin turbulent nonseparated flow p 474 A83-35933

Finite differecnce calcultion of an mviscid transonic flowover oscillating airtoils[AD-A123982] p 426 N83-25677


Flutter prediction in forward swept wings by assumedmodes and strip theory[AD-A124715] p 461 N83-25719

Some recent applications of XTRAIM3S[NASA-TM-85641] p 426 N83-26815


UPPER SURFACE BLOWINGApplications of advanced upper surface blowing



URBAN PLANNINGTransportation Energy Conservation Through Land Use

Planning[PB83-148387] p 475 N83-25919

URBAN TRANSPORTATIONTransportation Energy Conservation Through Land Use

Planning[PB83-148387] p 475 N83-25919

USER MANUALS (COMPUTER PROGRAMS)The remote link unit A demonstration of operational

performance Part 2 User's manual[AD-A124620] p 476 N83-25938

USER REQUIREMENTSStatus, trends and implications of carbon fiber material

use[PB83-147751] p 471 N83-26934

V/STOL AIRCRAFTThe history of V/STOL aircraft p 435 A83-36074Comparison of an experience with full authority digital

engine controls in rotary wing and |et-lift VSTOL aircraft[AIAA PAPER 83-1241] p 454 A83-36304



An assessment of factors affecting prediction ofnear-field development of a subsonic VSTOL jet incross-flow[AD-A124583] p 441 N83-25699

Advances in ejector technology A tnbute to Hans vonOham s vision p 477 N83-26B05


VANESThe effect of variation of diffuser design on the


VAPOR PRESSUREThermodynamics of organic compounds

[AD-A125022] p 483 N83-27895VARIABLE SWEEP WINGS


VECTORS (MATHEMATICS)Structural model tuning via vector optimization

[AD-A124791] p 477 N83-26103VELOCITY


VELOCITY DISTRIBUTIONThe performance of an annular vane swirler — to aid

in modeling gas turbine combustor flowfields and swirlingconfined flow turbulence[AIAA PAPER 83-1326] p 455 A83-36340

VENTSComputer studies of ACV heave performance as a

function of vent valve control parametersp 460 A83-34854

VERTICAL ORIENTATIONInvestigation of a third order baro-damped verticle

channel of INS[AD A124882] p 432 N83-26828

VERTICAL TAKEOFF AIRCRAFTEntramment and mixing in thrust augmenting ejectors

[AIAA PAPER 83-0172] p419 A83-36046A preliminary assessment of helicopter/VSTOL handling


VERY HIGH FREQUENCIESA rapid-tuning high-power pod-mounted VHP antenna

system p 430 A83-35088VHF OMNIRANGE NAVIGATION

A theoretical framework for analysis of lateral positionerrors in VOR let-route systems p 431 A83-35273

VIBRATION DAMPINGDesign of dry-friction dampers for turbine blades

p450 A83-35883VIBRATION EFFECTS

A theoretical framework for analysis of lateral positionerrors in VOR jet-route systems p 431 A83-35273

VIBRATION ISOLATORSExperimental investigation on the role of flexbars and


VIBRATION MEASUREMENTVibrational diagnostics of gas-turbine blades

p 473 A83-35040Modern technology and airborne engine vibration


VIBRATION MODEThe response of aircraft to pulse excitation

p 434 A83-34312Excitation and vibration of flexible bladed disks under

operating and simulated operation conditionsp449 AB3-35881


VIBRATION TESTSAircraft equipment random vibration test criteria based


VIBRATORY LOADSHigh frequency fatigue of turbine blade material

[AD-A124585] p 458 N83-25713VIDEO DISKS

Design of a real-time CGSI system[AIAA PAPER 83-1101] p 474 A83-36221

VISCOUS FLOWThe aerodynamics of hyposonic velocities (On flows with

low Mach numbers) p417 A83-35535Numencal calculations of time dependent

three-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-1171] p 420 A83-36258


VISUAL FLIGHTReal time simulation of mission environments for

avionics systems integration[AIAA PAPER 83-1097] p 463 A83-36217

VISUAL PERCEPTIONTheory underlying the peripheral vision horizon device

IAD-A124426] p 445 N83-25710Research and analysis of head-directed area-of interest

visual system concepts[NASA-CR-166480] p 467 N83 26849

VOIDSEvaluation of the effect of voids in composite mam rotor


blades P 435 A83-35950VORTEX FLAPS


VORTEX GENERATORSExperimental study of a high-through-flow transonic axial

compressor stage p 419 A83-35853VORTICES

Full-scale measurements of blade-vortex interactionnoise p 482 A83-33505

Recent studies at NASA-Langley of vortical flowsinteracting with neighboring surfaces

p417 A83 33972Calculation of subsonic flow past rectangular wings and


Full-scale measurements of blade-vortex interactionnoise p435 A83 35947


wWALL FLOW

Survey of the ONERA activities on the adaptive wallapplications and commutation of residual corrections[ONERA, TP NO 1983-11] p 464 A83 36421

WARNING SYSTEMSSandia Helicopter Acoustic Detector (SHAD)

[DE82-018925] p 483 N83-27803WATER TABLES

Design of choking cascade turns[AO-A124792] p 477 N83 26023

WAVESWind tunnel investigation of cargo extraction parachutes

in the wake of a Lockheed C-141B Starlifter aircraft[AD-A124523] p 425 N83 25675

WEAPON SYSTEMSUse of flight test results to improve the flying qualities

simulation of the 8-52H weapon system trainer[AIAA PAPER 83-1091 ] p 437 A83-36215



WEAPONS DELIVERYDynamics of air combat p 416 A83 36914

WEAR TESTSEccentric end wear in cylindrical roller bearings can be

predicted and prevented[AIAA PAPER 83-1132] p 474 A83 36237

WEATHERScanning strategies for next generation weather radars

A study based on lifetimes of convective atmosphencphenomena hazardous to aviation[FAA-RD-82-69] p 476 N83 25929

WEATHER FORECASTINGAnalysis and specification of slant wind shear

[AD-A125683) p 479 N83-26367WEDGES

Edge tones in high speed flows and their applicationto multiple-jet mixing p 482 A83 36077

WEIGHT REDUCTIONOptimization for structures of discrete-size elements

p472 A8334311WIDEBAND COMMUNICATION


WIND PROFILESAnalysis and specification of slant wind shear

[AD-A125883] p 479 N83 26367WIND SHEAR


WIND TUNNEL APPARATUSModel mount system for testing flutter

[NASA-CASE-LAR-12950-1] p 465 N83 25727

A-25

WIND TUNNEL MODELS SUBJECT INDEX

WIND TUNNEL MODELSSurvey of the ONERA activities on the adaptive wall

applications and commutation of residual corrections| ONERA, TP NO 1983 11] p 464 A83-36421

Wind tunnel test of a C 18 aircraft modified with theadvanced range instrumentation aircraft radome(AD-A124771) p 425 N83-25671

WIND TUNNEL TESTSRecent studies at NASA-Langley of vortical flows


The swirl in an S-duct of typical air intake proportionsp418 A83-35620

Separated flows on a concave conical wingp418 A83-35707

Development of a turboiet engine simulator for scalemodel wind tunnel testing of multi-mission aircraft

p 447 A83-35848Propulsion system simulation technique for scaled wind

tunnel model testing p 463 A83-35850STOL wind tunnel test results for a tactical

supercruiser[AIAA PAPER 83-1224J p 420 A83-36291


Ejector nozzle test results at simulated flight conditionsfor an advanced supersonic transport propulsion system| AIAA PAPER 83-1287] p 454 A83-36323






Effect of empennage location on twin-engineafterbody nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2 -- wind tunnel tests(NASA-TP-2116) p424 N83-25666

Wind tunnel investigation of varying hinged flaps[AD-A124703] ^ p 424 N83-25668

Transient heat transfer measurement technique in windtunnel and data analysis technique using systemidentification theory[AD-A124663] p 424 N83-25669

Wind tunnel test of a C-18 aircraft modified with theadvanced range instrumentation aircraft radome[AD-A124771] p 425 N83-25671

Force and pressure measurements on a research modelwith a low-, mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p425 N83 25676





WIND TUNNEL WALLSSurvey of the ONERA activities on the adaptive wall

applications and commutation of residual corrections[ONERA, TP NO 1983-11] p 464 A83-36421

WIND TUNNELSOptimum wire screens for control of turbulence in wind

tunnels p417 A83-33772A note on adaptive wind tunnels with imperfect control

p 466 N83-26792WIND TURBINES

Aerodynamic research on Ttpvane wmdturbmes[PB83-147413] p 479 N83-27476

WIND VANESAerodynamic research on Tipvane wmdturbmes

[PB83-147413] p479 N83-27476WIND VELOCITY


WING CAMBERAFTI/F-111 mission adaptive wing technology

demonstration program[AIAA PAPER 83-1057] p 438 A83-36468

WING FLOW METHOD TESTSWind tunnel tests of over-the-wmg nacelles — supported

on'stub-wings' p 422 A83-36916WING LOADING



WING NACELLE CONFIGURATIONSAerodynamic design of propfan powered transports

[AIAA PAPER 83-1213] p 437 A83-36285Wind tunnel tests of over-the-wing nacelles — supported

on'stub-wings' p 422 A83-36916WING PANELS


WING PROFILESSeparated flows on a concave conical wing

p418 A83-35707WING SLOTS


WING TIPSAnalysis of nonplanar wing-tip-mounted lifting surfaces


WINGLETSCF34 upgrades Challenger capabilities

p434 A83-35315Analysis of nonplanar wing-tip-mounted lifting surfaces


WINGSTheoretical determination of the lift of a simulated ejector

wing[AD-A124695] p 425 N83-25670

Force and pressure measurements on a research modelwith a low-, mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A 124068] p 425 N83-25676


WIREImpact damping and airplane towing


pattern p 439 A83-36919Verification testing of an AH-1S Wire Strike Protection

System (WSPS)[AD-A123188] p 429 N83-25684

WIRE CLOTHOptimum wire screens for control of turbulence in wind

tunnels p417 A83-33772

X-22A AIRCRAFTIndoctrination of Navy test pilots to vectored thrust flight

in the X-22A in-flight simulator[AIAA PAPER 83-1076] p 436 A83-36205

XV-15 AIRCRAFTA preliminary assessment of helicopter/VSTOL handling


YAWA static investigation of yaw vectoring concepts on

two-dimensional convergent-divergent nozzles[AIAA PAPER 83-1288) p 421 A83-36324

YIELD STRENGTHEvaluation of low-cost aluminum composites for aircraft


A-26

PERSONAL AUTHOR INDEX


Typical Personal AuthorIndex Listing

PERSONAL AUTHOR

BAEZ, A N— Arrny/NASA small turboshaft engine digital controlsresearch program(NASA-TM-82979) p 44 N83-11128

TITLEREPORTNUMBER

PAGENUMBER

NASAACCESSION

NUMBER

Listings in this index are arranged alphabetically bypersonal author The title of the document providesthe user with a bnef description of the subjectmatter The report number helps to indicate thetype of document listed (e g, NASA report,translation, NASA contractor report) The page andaccession numbers are located beneath and to thenght of the title Under any one author's name theaccession numbers are arranged in sequence withthe AIAA accession numbers appeanng first

ABBASY, IDetermination of stability and control parameters ot a

general aviation airplane trom flight data[NASA-TM-84635] P 461 N83-26844

ABDELMALIK, F IThe transient performance of turbojet engines and axial

compressors p 447 A83-35847

ABE, TVariation of rotor blade vibration due to interaction of

inlet and outlet distortion p 450 A83-35882

ABIBOV, A L.Aircraft production technology (2nd revised and enlarged

edition) p415 A83-36443

ADAM, C FClimatic laboratory survey Hughes YAH 64 helicopter

[AD-A124670] p440 N83-25698

ADAM, P WNASA low-speed centrifugal compressor for

fundamental research[AIAA PAPER 83-1351 ] P 464 A83-36353

NASA low-speed centrifugal compressor forfundamental research[NASA-TM-83398] P 424 N83-25662

ADKINS, R PData base considerations for a tactical environment

simulation[AIAA PAPER 83-1099J P 463 A83-36219

AGGARWAL, H RDerivation of the fundamental equation of sound


AHMAD, IDesign and analysis of a subcritical airfoil for high

altitude long endurance missions[AD-A124757] p 441 N83-25702

ALBERS, GAdvanced display techniques for training the

multi-member tactical air crew[AIAA PAPER 83-1079] P 443 A83-36207

ALEKSANDROV, V VAn algorithm of flight simulation on a dynamic stand of

support type P 462 A83-34429

ALJABRI, A SAerodynamic design of propfan powered transports

[AIAA PAPER 83-1213) p 437 A83-36285ALLAN, J , III

Instrumental problems m small gas turbine engines[AIAA PAPER 83-1293] p 444 A83-36327

ALLEY, W R , JRA Monte Carlo simulation of the engine development


Technology and engine demonstrator programs[AIAA PAPER 83-1064] p 457 AB3-36464

ALMASSY, R JExperimental analysis of the performance of an annular

peripheral jet vehicle in ground effect[AD-A124949] p 443 N83-26832

ALZIAL, HOmega application in the Indonesian region

p431 A83-35599AMATO, A J

Dynamic modeling of an air cushion vehiclep486 A83-35054

AMEND, J BThe effects of the Production Oriented Maintenance


AMIN, N FThrust reverser exhaust plume Reingestion tests for a


AMYOT, J RComputer studies of ACV heave performance as a

function of vent valve control parametersp 460 A83 34854

Computer studies of ACV heave dynamics stabilizationp 486 A83-35055

ANCONA, WDesign of dry-friction dampers for turbine blades

p450 A83-35883ANDERSON, R D

Advanced propfan engine characteristics andtechnology needs[AIAA PAPER 83-1155] p 450 A83 36250

ANDERSON, R EAircraft engine inlet pressure distortion testing in a


ANDERSON, S BPilot human factors in stall/spin accidents of supersonic

fighter aircraft[NASA-TM-84348] p 462 N83-26846

ANDO, SImproved numerical method for unsteady lifting surfaces

in incompressible flow p 422 A83-36917ANTOLOVICH, S D

The effect of microstructure on the fatigue behavior ofNi base superalloys p 469 A8336166

ANTONENKO, A IThe motion dynamics of parachute systems

p422 A83-36450ARLOWE, H D

Sandia Helicopter Acoustic Detector (SHAD)[DE82-018925] p483 N83 27803

ARMSTRONG, F EFrom new technology development to operational

usefulness B-36, B-58, F 111 /FB-111[AIA PAPER 83-1046] p415 A83-36459

ARNTZEN, D MGuidance control systems for aircraft on airport

surfaces(AIAA PAPER 83-1579] p 429 A83-36953

ASCHMANN, S MHigh altitude jet fuel photochemistry

[AD-A125035] p 471 N83-27035ASHFORD, R L


ASHKENAS, I LProposed MIL standard and handbook Flying qualities


ASHMOLE, P JIntroducing the Rolls-Royce Tay

[AIAA PAPER 83-1377]ATKINSON, R

High altitude |et fuel photochemistry[AD-A125035]

p 456 A83-36368

p 471 N83-27035

AUERBACH, ISome applications ot ultrasonic methods for the quality

control of nonmetallic objects p 475 A83-36794

AUSTIN, C JThe Dash 8 development program

p433 A83-33546 i

BBAGANOFF, D

Edge tones in high-speed flows and their applicationto multiple-jet mixing p 482 A83-36077

BAHR, D WMethanol combustion in a CF6I-80A engine combustor

[AIAA PAPER 83-1138] p 469 A83-36241

BAILEY, R ELateral flying qualities of highly augmented fighter

aircraft, volume 1[AD-A118070] p443 N83-26835 I

BAIRD, JDesign of choking cascade turns

[AD-A124792] p 477 N83-26023BAKER, A J

An assessment of factors affecting prediction ofnear-field development of a subsonic VSTOL jet incross-flow[AD-A124583] p 441 N83-25699

BALAN, CEffect of sand erosion on the performance deterioration

of a single stage axial flow compressorp448 A83-35854

BALCH, D TExperimental study of mam rotor/tail rotor/airtrame


BALD, W BTemperature response of a model to set-point changes

and conditioning in ETW p 465 N83-25721BALDWIN, D M

Design ot a real-time CGSl system[AIAA PAPER 83-1101] p 474 A83-36221

BALICKI, WElectrohydraulic fuel-flow regulator for

gas-turbine-engine control systems p 458 A83-36793BALL, W H

Experimental investigation of the effects of wall suctionand blowing on the performance of highly offsetditfusers[AIAA PAPER 83-1169] p 423 A83-36922

BAND, E G UA design synthesis model for ACV/SES lift systems

p486 A83-35057BARNHART, B

F-14 rotary balance tests tor an angle-of-attack rangeof 0 deg to 90 deg[AD-A124468] p 441 N83-25700

BARNHILL, R ESurfaces in computer aided geometric design.

Proceedings of the Conference Oberwolfach, WestGermany, Apnl 25-30, 1982 p 480 A83-33613

BARRETT, R JDeterioration trending enhances jet engine hardware


BARTLETT, GMethod for calculating effects of a propfan on aircraft

aerodynamics at subsonic speeds(AIAA PAPER 83-1216] p 420 A83-36287

BEATTIE, J A CA true air speed sensor for miniature unmanned

aircraft p 444 A83-36613

B-1

BECK, C L, JR PERSONAL AUTHOR INDEX

BECK, C L,JRAirframe RDT&E cost estimating A justification for and

development of unique cost estimating relationshipsaccording to aircraft type[ADA123848] p417 N83-25656

BEGIN, LThe Northrop Flying Wing prototypes

|AIAA PAPER 83-1047] p416 A83-36471BEILMAN, J L


BELL, W AAerodynamic measurements about a rotating propeller

with a laser velocimeter[AIAA PAPER 83-1354] p 421 A83-36355

BENDER, G LClimatic laboratory survey Hughes YAH-64 helicopter

[AD-A124670] p 440 N83-25698BENNETT, H W

Advanced turboprop and dual cycle engine performancebenefits and installation options on a Mach 0 7 shorthaultransport aircraftIAIAA PAPER 83-1212] p 452 A83-36284

BENNETT, R MSome recent applications of XTRAN3S

[NASA-TM-85641] p 426 N83-26815BERENFELD, A

Experiments in dilution jet mixing[AIAA PAPER 83-1201 ] p 475 A83-36277

BERENYI, S GAn update on high output lightweight diesel engines for


BERNAL, LEntramment and mixing in thrust augmenting ejectors

[AIAA PAPER 83-0172] p 419 A83-36046BERRIER, B L

Empennage/afterbody integration for single andtwin-engine fighter aircraft[AIAA PAPER 83-1126] p 420 A83-36235

A static investigation of yaw vectoring concepts ontwo-dimensional convergent-divergent nozzles[AIAA PAPER 83 1288] p 421 A83-36324

BHARGOV, P K RThe response of aircraft to pulse excitation

p 434 A83-34312BILLIG, F S

International Symposium on Air Breathing Engines, 6th,Pans, France, June 6-10 1963, Symposium Papers

p 445 A83-35801Applications of computational techniques in the design

of ramjet engines p 418 A83-35828BIRIUKOV, N M

Aircraft production technology (2nd revised and enlargededition) P415 A83-36443

BIRKEN, J AComposite material aircraft electromagnetic properties

and design guidelines[AD-A124016] P470 N83-25795

B1RKLER, J L.Development and production cost estimating


BLACKALLER, D LDevelopment and application of a liquid-cooled V-8

piston engine for general aviation aircraft[AIAA PAPER 83-1342] p 455 A83-36347

BLACKMORE, W LThree-dimensional compressible viscous analysis of


BLANCHARD, AProblems involved by the instrumentation and the

conception of cryogenic tests p 465 N83-25725BOEHM, W

Surfaces in computer aided geometnc design,Proceedings of the Conference, Oberwolfach, WestGermany, April 25-30, 1982 p 480 A83-33613

BOGAR, T JResponse of a supersonic inlet to downstream


BOITSOV, V VAircraft production technology (2nd revised and enlarged

edition) p415 A83-36443BOUDREAULT, J


BOWDEN, J NEmergency fuels technology

[AD-A125275) p471 N83-25904BOWERS, D L.


Definition of vectored nonaxisymmetnc nozzle plumes[AIAA PAPER 83-1290] p 423 A83-36924

BOXWELL, 0 AFull scale measurements of blade-vortex interaction

noise p482 A83-33505Full-scale measurements of blade-vortex interaction

noise p 435 A83-35947BOZICH, R

Precision navigational filmstnps for use in DOD aircraft[AD-A124761] p 432 N83-25688

BRADEN, J AExperimental studies of the separating confluent


BRAMER, J RAn investigation of the effectiveness of smoke


BRANDEAU, GThe application of low-cost demonstrators for


BRANDES, DFeasibility of dry lubrication for limited-duty gas turbine


BRAYBROOK, RAircraft design philosophy I - Lee Begin of Northrop

p 434 A83-35624BRENNER, L

Materials in the mirror of aviation criteriap434 A83-33952

BRESNAHAN, D LElector nozzle test results at simulated flight conditions

for an advanced supersonic transport propulsion system[AIAA PAPER 83-1287) p 454 A83-36323

BREUGELMANS, F A EFlow in rotating stall cells of a low speed axial flow

compressor p 419 A83-35874BRIEHL, D


BRISTOW, D RAircraft aerodynamic prediction method for V/STOL

transition including flow separation[NASA-CR-166467] p 426 N83-26818

BROUWERS, A P"An update on high output lightweight diesel engines for


BROWDER, G BSimulator performance definition by cue synchronization

analysisIAIAA PAPER 83-1092] p 463 A83-36216

BROWN, A MHigh frequency fatigue of turbine blade material

[AD-A124585] p 458 N83-25713BROWN, D D

USAF mobility requirements[AIAA PAPER 83-1588] p 429 A83-36954

BROWN, H AAnalysis and specification of slant wind shear

(AD-A125883] p 479 N83-26367BROWN, P W


BROWN, S CA flight-test and simulation evaluation of the longitudinal

final approach and landing performance of an automaticsystem for a light wing loading STOL aircraft[NASA-TM-84270] p 461 N83-26845

BROWNING, R G E1983 LTA technology assessment

| AIAA PAPER 83-1617] p 437 A83-36406BUCK, M L


BUCKANIN, R MAirworthiness and flight characteristics test Part 2


BUGGELE, A ENASA low-speed centrifugal compressor for

fundamental research| AIAA PAPER 83-1351] p 464 A83-36353


BUNK, WHighly stressed materials, with aviation considered as

an example p 467 A83-33951

BURKE, M PApplication of a finite difference method to the transonic

airfoil problem[AD-A124720] p 425 N83-25674

BURROWS, C RA modified algorithm for determining structural

controllability p 480 A83-36455BURROWS, L T


BURSTADT, P LExperimental results of a deflected thrust V/STOL


BUSCHULTE, WThe effect of fuel atomization on soof-free combustion

in a prevaporizmg combustor p 446 A83-35812BUTRIMAS, S K

Simulator performance definition by cue synchronizationanalysis[AIAA PAPER 83-1092] p 463 A83-36216

BUZZELL, W AThe use of vortex generators as inexpensive compressor

casing treatment p 459 N83-26798

CALLAHAN, C JA high speed wind tunnel test evaluation of STOL


CAMPBELL, G SCanadian forces tracker aircraft full-scale fatigue test

at the national aeronautical establishmentp 433 A83 33548

CAMPBELL, J FRecent studies at NASA-Langley of vortical flows


CAO, M -HFurther study on the prediction of liquid fuel spray capture

by v-gufter downstream of a plain orifice injector underuniform cross air flow p 473 A83-35810

CAPONE, F JEffects of varying podded nacelle-nozzle installations

on transonic aeropropulsive characteristics of a supersonicfighter aircraft[NASA-TP-2120] p 427 N83 26821

CARDULLO, F MOld problem/new solutions - Motion cuing algorithms


CARLIN, C MInlet, engine, airframe controls integration development

for supercruismg aircraft p 447 A83-35842CARR, L W


CARTER, P WGeneral aviation activity and avionics survey

[AD-A124595] p416 N83-25653CARTER, T J , III


CARTER, W P LHigh altitude jet fuel photochemistry

[AD-A125035] p 471 N83-27035CASALINI, F

Flow in rotating stall cells of a low speed axial flowcompressor p419 A83-35874

CASSMEYER, C CPropulsion system simulation technique for scaled wind

tunnel model testing p 463 A83-35850CASTELLS, O T

Accelerated Mission Testing of the F110 EngineIAIAA PAPER 83-1235] p 453 A83-36298

CASTOR, J GCompound cycle turbofan engine

IAIAA PAPER 83-1338] p 455 A83-36346CEA, R A

Fighter engine cycle selectionIAIAA PAPER 83-1300] p 457 A83-36412

CEBECI, TCalculation of boundary layers near the stagnation point

of an oscillating airfoil(NASA-TM-84305] p 478 N83-27148

CHANDRASEKARAN, BMethod for calculating effects of a propfan on aircraft

aerodynamics at subsonic speeds[AIAA PAPER 83-1216] p 420 A83-36287

CHANG, Y -ZExperimental research of the mechanism of flame

stabilization in two phase mixture p 469 A83-35822

B-2

PERSONAL AUTHOR INDEX DURSTON, D. A.

CHAO, D FNumerical simulation of electrothermal de-icing


CHEN, A WPAN AIR applications to aero-propulsion integration

(AIAA PAPER 83-1368] p 421 A83-36364CHEN, L T


CHENG, PEffects of compressor hub treatment on stator stall


CHETTA, G EEccentric end wear in cylindrical roller bearings can be

predicted and prevented(AIAA PAPER 83-1132] p 474 A83-36237

CHEVALLIER, J PSurvey of the ONERA activities on the adaptive wall

applications and commutation of residual corrections[ONERA, TP NO 1983-11] p 464 A83-36421

CHIN, J SFurther studies on the prediction of spray evaporation

rates p 468 A83-35811CHIN, J -S

Further study on the prediction of liquid fuel spray captureby v-gutter downstream of a plain orifice injector underuniform cross air flow p 473 A83-35810

CHRISTOPHE, JNew transformations of S4 Modane hypersonic wind

tunnel for ramjet missiles tests(ONERA, TP NO 1983-24] p 464 A83-36433

CHUDAREV, P FAircraft production technology (2nd revised and enlarged

edition) p415 A83-36443CHUGUNOV, O 0


CHURKIN, V MThe motion dynamics of parachute systems

p 422 A83-36450CHYLA, A


CLUBINE, W RModeling the helmet-mounted sight system

[AD-A124681] p 444 N83-25709COAKLEY, T J


COCHRANE, J AApplications of advanced upper surface blowing


COE, R JA network formulation for phased arrays Application

to log-periodic arrays of monopoles on curved surfacesp 431 AB3-35090

COHN, R BIn-flight acoustic test results for the SR-2 and SR-3


COLEMAN, NMicroprocessor-based optimal controllers for a

helicopter turret control system p 434 A83-35138COLLINS, H M

The remote link unit A demonstration of operationalperformance Part 3 Design manual, volume 1[AD-A124621] p476 N83-25934




COLLOM, R RThrust performance of a vanable-geometry, divergent

exhaust nozzle on a turbojet engine at altitude[NASA-TP-2171] p459 N83-26839

COMPTON, MDefinition of vectored nonaxisymmetnc nozzle plumes

[AIAA PAPER 83-1290] p 423 A83 36924CONNELL.D O

Multimode planar spiral for DF applicationsp 430 A83-35089

COOPER, R AGenerating an out the-wmdow cockpit image with the

lAPX 432i AD-A124852] p 466 N83-25735

CORONEL, P KConcepts for increased power and enhanced fuel


CORTEN, F L. J HPerformance capabilities of photographic flight

navigation and sensor orientation systemsp431 A83-36122

COWAN, J PInvestigation of the coupling of unsteady lift to low order


COWIE, W ODevelopment trends in engine durability

[AIAA PAPER 83-1297] p 455 A83-36329COX, R A

Force and pressure measurements on a research modelwith a low-, mid- and T-tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p 425 N83-25676

COY, P FNatural laminar flow data from full-scale flight and

wind-tunnel experiments p 422 A83-36409CRAIG, J E


CRAIG, R RCoaxial dump combustor investigations

p 459 N83-26791CRANE, D F

Compensation for time delay in flight simulatorvisual-display systems[AIAA PAPER 83-1080] p 464 A83-36222

CROUCH, K EAircraft lightning-induced voltage test technique

developments[NASA-CR-170403) p 442 N83-26829

CRUZEN, LCruise missile propulsion versus commercial airliner


CULY, 0 GMonte Carlo simulation of the engine development


CURRERI, P APreliminary science report on the directional solidification


CURRY, CAspects o1 the T56 power section usage/operating

costs[AIAA PAPER 83 1408] p 457 A83-36397

DAS, D KA study of the response of a turbojet engine to the inlet

temperature transients p 448 A83-35849Flow measurements within rotating stall cells in single


DA VIES, W JFlight/propulsion control system integration

[AIAA PAPER 83-1238] p 453 A83-36301DAVIS, J B

Criteria for optimizing starting cycles for highperformance fighter engines[AIAA PAPER 83-1127] p 450 A83-36236

DAVIS, R APressures measured in flight on the aft fuselage and


DAVIS, S PAccelerated simulated mission endurance test of a

turboshatt engine tor military attack helicopterapplication[AIAA PAPER 83-1359] p 455 A83-36357

DE WITT, K JNumerical simulation of electrothermal de-icing


DEJONG, JComputation of incompressible potential flow over an

airfoil using a high order aerodynamic panel method basedon circular arc panels(AD-A124896] p 428 N83-26825

DERBUNOVICH, G IOptimum wire screens for control of turbulence in wind

tunnels p417 A83-33772

DEVORE, C RStructural model tuning via vector optimization

[AD-A124791] p 477 N83-26103DEWAAL, J F

Canadian forces tracker aircraft full-scale fatigue lestat the national aeronautical establishment

p 433 A83-33548Dl RUSSO, EL

Design analysis of a self-acting spiral-groove ring sealfor counter-rotating shafts(AIAA PAPER 83-1134] p 474 A83-36239

DILL, JFeasibility of dry lubrication for limited-duty gas turbine


DIRUSSO, EDesign analysis of a self-acting spiral-groove ring seal

for counter-rotating shafts[NASA-TP-2142] p 458 N83-25712

DMITRIEV, A AThe Ka-26 helicopter p 437 A63-36448

DOANE, P MF/A-18A Inflight Engine Condition Monitoring System


DOBBS, G MCARS temperature and species measurements in

augmented jet engine exhausts[AIAA PAPER 83-1294] p 455 A83-36328

DOCKEN, R G , JRGust response prediction of an airfoil using a modified


DODDS, W JMethanol combustion in a CF6I-80A engine combustor

[AIAA PAPER 83-1138] p 469 A83-36241OOLEZAL, Z


p 449 A83-35881DOMALSKI, J T


DOONAN, J GA high speed wind tunnel test evaluation of STOL


DOTSENKO, Y NMethod of studying the operating temperature of gas

turbines[PNR-90159] p460 N83-26842

DOWELL, E HDesign of dry-friction dampers for turbine blades

p 450 A83-35883DOWNS, G T


DRAPER, A CAerospace technology demonstrators/research and

operational options[AIAA PAPER 83-1054] p 438 A83-36465

DREHER, J FAircraft equipment random vibration test criteria based


DRESS, D AHigh Reynolds number tests of the CAST 10-2/DOA 2

airfoil in the Langley 0 3-meter transonic cryogenic tunnel,phase 1[NASA-TM-84620] p 424 N83-25660

DREVILLON, MVectored thrust afterbody nozzles for future combat

aircraft p 448 A83-35859DREWRY, J E


DREXLER, JA contnbution to airworthiness certification of gas turbine

disks p 449 A83-35872DUEKER, M


DUFF, W GComposite matenal aircraft electromagnetic properties


DUPRIEZ, FMaterials and modelling technology for cryogenic

environment p 465 N83-25723DURSTON, 0 A


p 474 A83-36085

B-3

DUSA, C. J. PERSONAL AUTHOR INDEX

DUSA, C JPerformance capability of a Compact Multimission

Aircraft Propulsion Simulator[AIAA PAPER 83 1358] p464 A83-36356

DUSA, D JDevelopment of a turbojet engine simulator for scale


DYKE, R WDevelopments in air cushion vehicle spray

suppression p 486 A83-35056DYLEVSKII, I V


EASTOP, T DThermal cycling in compact plate-fin heat exchangers

p 445 A83-34253ECCLES, E S

Comparison of an experience with full authority digitalengine controls in rotary wing and jet-lift VSTOL aircraft| AIAA PAPER 83 1241J p 454 A83-36304

ECKBRETH, A CCARS temperature and species measurements in


EHRESMAN, C MEffect of humidity on |et engine axial-flow compressor

performance p 448 A83-35856EKSTEDT, E E

Metha.no! combustion in a CF6I-80A engine combustor[AIAA PAPER 83-1138] p 469 A83-36241

EL SIBAIE. A MThe effect of variation of diffuser design on the


ELDREDGE, DDigital flight control system validation

[AD-A124506] p 462 N83-26847ELLE, B J

Worldwide aviation outlook(AIAA PAPER 83 1597] p 429 A83-36952

EMERSON, L. DFlight/propulsion control system integration

[AIAA PAPER 83-1238] p 453 A83-36301EMMAS, D E


ENDEMANN, DMaterial, structural component, service life

p468 A83-33953ENEVOLOSON, E K


ERIKSEN, L EThe effects of the Production Oriented Maintenance


ESSLINGER, PMaterial, structural component, service life

p 468 A83-33953EVERETT, K N


p 474 A83-36085

FARDINK, P JHand-held computer programs for preliminary helicopter

design[AD-A125036] p 481 N83-27624

FARMER, M GModel mount system for testing flutter

[NASA-CASE-LAR-12950-1] p 465 N83-25727FATYKHOV, F F

The motion dynamics of parachute systemsp 422 A83-36450

FELLERS, W EThe F-5 story -_ Prototype and technology

demonstrator[AIAA PAPER 83-1062] p 439 A83-36473

FER, RVectored thrust afterbody nozzles for future combat

aircraft p 448 A83-35859FERGUSON, J A , III


FLATHERS, G W , IIFAA integrated noise model validation Analysis of air


FLETCHER, R SEffect of air, liquid and injector geometry variables upon

the performance of a plam-|et airblast atomizerp 473 A83-35809

FORD, R LOn the use of height rules in off-route airspace

p 431 A83-35274FOWLER, H S

ACV lift air systems - More puff for less powerp 485 A83-34861

Skirts - Time for a new look' p 486 A83-35058FOX, T G


FOY, T FPropulsion prototypes at general electric

[AIAA PAPER 83-1053] p 457 A83-36463FRASER, K F


FREEMAN, W GFurther studies on the prediction of spray evaporation

rates p 468 A83-35811FRICKE, H

Design and development of a small gasturbine engineResults today - A basis for design criteria of a nextgeneration p 446 A83-35829

FRIEDMANN, P PCoupled flap-lag-torsional dynamics of hingeless rotor

blades in forward flight p 433 A83-33506Coupled flap-lag-torsional dynamics of hingeless rotor

blades in forward flight p 435 A83-35948FROMMEYER, H

Structural members made of high-strength castaluminum and their properties p 468 A83-33954

FUOUN, CThe prediction of performance of turbojet engine with


Prototype and technology

p 439 A83-36473

GALLAGHER, J TThe F-5 story -

demonstrator[AIAA PAPER 83-1062]

GALLOWAY, R TFlight fidelity testing of the F/A-18 simulators

[AIAA 83-1094] p 437 A83-36225GAMMON, B E

Thermodynamics of organic compounds[AD-A1 25022] p 483 N83-27895

GAOLIAN, L.Aerodynamic optimization theory of A 3-D axial-flow

rotor-bladmg via optimal control p 418 A83-35839GARBEROGLIO, J E

Maximum loading capability of axial flow compressors[AIAA PAPER 83-1 163] p 451 A83-36254

GARFINKLE, J BDevelopment and production cost estimating


GAWISH, DTechnical aspects of the AEROBAC AB-7

p 484 A83-34858GEBHARD, E P


GENTIL, PDesign and development of a nozzle extendible exit

cone[AIAA PAPER 83-1410] p 467 A83-36399

GERNER, A ASeven-hole cone probes for high angle flow


GIAMATI, C CDynamic distortion in a short s-shaped subsonic diffuser

with flow separation[NASA-TM-84312] p 459 N83-26838

GILL, J CAdvanced propfan engine charactenstics and

technology needs[AIAA PAPER 83-1155] p 450 A83-36250

GILMER, B RAircraft aerodynamic prediction method for V/STOL

transition including flow separation[ N AS A-CR- 166467] p 426 N83-26818

GINZBURG, A EThe use of a structural model for determining the

adaptability curve for turbine disks m stress concentrationzones % p 445 A83 35039

GLASER, F WLow flight speed acoustic results for a supersonic inlet

with auxiliary inlet doors[NASA-TM-83411] p 482 N83-27794

GLICKSTEIN, M RThermal stability of alternative aircraft fuels

[AIAA PAPER 83-1143] p 470 A83-36243GLOVER, J R,JR


The remote link unit A demonstration of operationalperformance Part 3 Design manual Volume 2Appendices A C[AD-A124622] p 476 N83 25935


The remote link unit A demonstration of operationalperformance, part 1[AD-A124619] p 476 N83 25939

GOCI, M JAn interactive bombing mission simulation with computer

graphics interface[AD-A124661] p 481 N83-26637

GOLDIEZ, B FDesign of a real-time CGSI system

[AIAA PAPER 83-1101] p 474 A83 36221GOLDMAN, A


GOLDSTEIN, KA preliminary assessment of helicopter/VSTOL handling


GONULLU, BNumerical treatment of Doppler radar signals

IENST-E-82014] p 478 N83-27114GOODMAN, R C


GOSSEN, J JMonte Carlo simulation of the engine development


GOVARDHAN, MEffect of entry boundary layer thickness on secondary

flows in an annular cascade of turbine nozzle and rotorblades p 419 A83-35868

GOYAL, R KThree-dimensional compressible viscous analysis of


GRAF, C PDesign of a real-time CGSI system

[AIAA PAPER 83-1101] p 474 A83 36221

GRAHAM, T AApplication of system identification flight analysis


GREGG, GCost effective performance restoration of high by-pass

engines p 447 A83-35833

GREITZER, E MEffects of compressor hub treatment on stator stall


GRIFFIN, M DApplications of computational techniques in the design

of ramjet engines p418 A83-35828

GRIGOREV, V PAircraft production technology (2nd revised and enlarged

edition) p415 A83-36443

GROESBECK, D EJT150 1/2-scale nozzle jet noise experiment and

comparison with prediction[NASA-TM-83370] p 482 N83 27793

GSCHWENDER, L JDetermination of the sensitivity of U S Air Force aircraft


GUILLARD, POmega application in the Indonesian region

p 431 A83-35599

QUO, R WThe swirl in an S-duct of typical air intake proportions

P418 A83-35620

B-4

PERSONAL AUTHOR INDEX

HHAAS, M W

Visually-coupled systems as simulation devices[AIAA831083I P 464 A83-36224

HAGER, R DThe aerodynamic design and performance of the

General Electric/NASA EEE fan[AIAA PAPER 83-1160] P 451 A83-36252

HAN, l_ STransient heat flow along uni-directional fibers in

composites[AD-A122926] P 471 N83 26929

HANIF, S MA review and comparison of lightning return stroke

models using expenmental data[AD-A124680] P 479 N83-26345

HANSEN, B JAutomatic control and data acquisition system for

combustion laboratory applications[AD-A125195) P 470 N83-25829

HANSEN, JHighly stressed materials, with aviation considered as

an example P 467 A83-33951HARDY, G H

A flight-test and simulation evaluation of the longitudinalfinal approach and landing performance of an automaticsystem for a tight wing loading STOL aircraft[NASA-TM 84270] P 461 N83-26845

HARDY, RAFTI/F-111 mission adaptive wing technology

demonstration program[AIAA PAPER 83-1057] P 438 A83-36468

HARRIS, W R,JRDeterioration trending enhances jet engine hardware

durability assessment and part management[AIAA PAPER 83-1234] P 453 A83-36297

HART, R HSH-3 helicopter/Global Positioning System integration

analysis[AD-A125005] P 432 N83-25691

HARTMANN, P VApplication of system identification flight analysis

techniques to the pitch-heave dynamics ol an air cushionvehicle P 484 A83-34852

HARVELL, J KAn experimental/analytical investigation into the

performance of a 20-percent thick, 8 5-percent cambered,circulation controlled airfoil[AD-A124732] P 441 N83-25701

HAYS, A PAdvanced turboprop and dual cycle engine performance

benefits and installation options on a Mach 0 7 shorthaultransport aircraft[AIAA PAPER 83-1212] P 452 A83-36284

HEAD, VThree-dimensional compressible viscous analysis of

mixer nozzles[AIAA PAPER 83-1401] P 422 A83-36391

HEFFLEY, R KProposed MIL standard and handbook Flying qualities

of air vehicles Volume 2 Proposed MIL handbook[AD-A123726] P 441 N83-25704

HEIDELBERG, L JA compact inflow control device for simulating flight fan

noise[NASA-TM-83349] P 482 N83-26643

HELM, R WOperational deployment of the air cushion vehicle

P485, A83-34864From Voyageur on - The exploitation of an opportunity

to develop a Canadian air cushion vehicle industryp 485 A83-35052

HENDRIX, J CPreliminary science report on the directional solidification

of hypereutectic cast iron during KC-135 low-Gmaneuvers[NASA-TM-82528] P 470 N83-25854

HERBST, W BDynamics of air combat P416 A83-36914

HERROUIN, GTechnical aspects of the AEROBAC AB-7

p 484 A83-34858HEHSTINE,G l_

Advanced turboprop and dual cycle engine performancebenefits and installation options on a Mach 0 7 shorthaultransport aircraft[AIAA PAPER 83-1212] P 452 A83-36284

HIDGKINSON, JProposed MIL standard and handbook Flying qualities

of air vehicles Volume 2 Proposed MIL handbook(AO-A123726] P 441 N83 25704

HILL, R JLCC evaluation of advanced engine damage tolerance

goals for a hot section disk[AIAA PAPER 83-1407] p 456 A83-36396

HILLAKER, H JThe F-16 - A technology demonstrator, a prototype, and

a flight demonstrator[AIAA PAPER 83 1063] p 438 A83-36467

HINCHEY, M JAn over view of UTIAS research on the dynamic stability

of air cushion vehicles p 484 A83-34853HINDSON, W S


HITT, EDigital flight control system validation

[AD-A124506] p 462 N83-26847HODGSON, B

A rapid-tuning high-power pod-mounted VHF antennasystem p 430 A83-35088

HOH, R HBring cohesion to handling-qualities engineering

p434 A83-35772Proposed MIL standard and handbook Flying qualities

ot air vehicles Volume 2 Proposed MIL handbook[AD-A123726] p 441 N83-25704

HOLDEMAN, J 0Experiments in dilution jet mixing

[AIAA PAPER 83-1201 ] p 475 A83-36277HOLMES, B J


HOMYAK, LA compact inflow control device for simulating flight fan

noise[NASA-TM-83349] p 482 N83-26643

HOPCROFT, R GProgress toward the analysis ot complex propulsion


HORATTAS, C GData base considerations for a tactical environment


HOUCHARD, J HInlet, engine, airtrame controls integration development

for supercruismg aircraft p 447 A83-35842HOUGHTON, W W

Evaluation of the effect of voids m composite mam rotorblades p 472 A83-33507

Evaluation of the effect of voids in composite mam rotorblades p 435 A83-35950

HSIA, YEdge tones in high-speed flows and their application

to multiple-jet mixing p 482 A83-36077HSU, D A

A theoretical framework for analysis ol lateral positionerrors in VOR jet-route systems p 431 A83-35273

HUA, H MOptimization for structures of discrete-size elements

P472 A83-34311HUILI, S

The prediction of performance of turboiet engine withdistorted inlet flow and its experimental studies

p 446 A83-35832HUNTER, D T

LCC evaluation of advanced engine damage tolerancegoals for a hot-section disk(AIAA PAPER 83-1407] p 456 A83-36396

HURRY, M FUnited Kingdom military engine usage, condition and

maintenance systems experience[AIAA PAPER 83-1239] p 453 A83-36302

HUSON, G G.Wind tunnel investigation of cargo extraction parachutes


HUSSEIN, G AEffect of air, liquid and injector geometry variables upon

the performance of a plain-jet airblast atomizerp 473 A83-35809

HUTCHISON, R ASTOL wind tunnel test results for a tactical


HWANG, CAircraft active controls - New era in design

p 461 A83-35773

I

IARKOVETS, A IAircraft production technology (2nd revised and enlarged

edition) P415 A83-36443ICHIKAWA, A


KARAMCHETI, K

IGUMENTSEV, E AVibrational diagnostics of gas-turbine blades

p 473 A83-35040IOFFE, G I

The Ka-26 helicopter p 437 A83-36448ISHIGURO, T


IUGOV, O KSome aspects of development of power plant optimum


IURTSEV, IU NThe motion dynamics of parachute systems

p 422 A83-36450

JANISSE, T CA parametric study of surface imperfections and small

cutouts in a composite panel[AD-A124739] p 470 N83-25793

JANSSEN, T LProgress in propulsion system/airframe structural


JASPAL, RCost effective performance restoration of high by pass

engines p 447 A83-35833JASUJA, A K

Effect of air liquid and injector geometry variables uponthe performance of a plain-jet airblast atomizer

p473 A83-35809JAYARAMAN, N


JENKINS, R MA comprehensive method for preliminary design

optimization of axial gas turbine stages II - Codeverification[AIAA PAPER 83-1403] p 456 A83-36393

JIANG, H KFlow measurements within rotating stall cells in single

and multistage axial-flow compressorsp 419 A83-35873

JIANG, L YA study of lean extinction limit for pilot flame holder

p469 A83-35821JOANNIC, Y


JOHNS, A LExpenmental results of a deflected thrust V/STOL


JONES, A, JRHow to improve air cushion vehicle performance with

VUMP equipped wave-forming keelsp484 A83-34855

JONES, G SExperimental studies of the separating confluent


JONES, KStatic aeroelastic analysis of flexible wings via

NASTRAN, part 1[AD-A124662] p 477 N83-26099

JONES, W PTemperature and composition measurements in a


KAFKA, JInvestigation methods on residual stresses in aero

engines components p 449 A83-35879KALLIO, R U

Modern technology and airborne engine vibrationmonitonng systems[AIM PAPER 83-1240] p 444 A83-36303

KAMSTRA, PFeasibility of dry lubncation for limited-duty gas turbine


KARAMCHETI, KEdge tones in high-speed flows and their application

to multiple-jet mixing p 482 A83-36077

B-5

KARCHMER, A M. PERSONAL AUTHOR INDEX

KARCHMER, A MAcoustic modal analysis of a full-scale annular

combustor[ AIAA PAPER 83-0760] p 481 A83-33486

KARPOVICH, P AEffect of fuel composition on Navy aircraft engine hot

section components(AIAA PAPER 83-1147) p 450 A83-36244

KAUSHAL, S CExperimental investigation on the role of flexbars and

metallic end seals in squeeze film dampersp473 A83 35862

KAWASHIMA, TResidual life prediction for |et engine rotor disks at

elevated temperature p 472 A83-33974KAZIN, S B

KC-135/CFM56 re engine The best solution[ AIAA PAPER 83-1374 ] p 456 A83 36367

KEITH, T GNumerical simulation of electrothermal de-icing


KELLERER, HMaterials in the mirror of aviation criteria

p 434 A83-33952KERN, P R A

Progress toward the analysis of complex propulsioninstallation flow phenomenon(AIAA PAPER 83-1367] p 421 A83-36363

KESLER, D FAircraft active controls - New era in design

p 461 A83-35773KINLEY, W R

F/A-18A Inflight Engine Condition Monitoring System(IECMS)[AIAA PAPER 83-1237J p 453 A83 36300

KJELGAARD, S OEvaluation of a surface panel method coupled with

several boundary layer analysesI AIAA PAPER 83-0011] p 474 A83-36039

KLASSEN, D DConfiguration selection and technology transition in 5000

SHP class enginesI AIAA PAPER 83-1411 ] p 457 A83-36400

KLEIN, R HProposed MIL standard and handbook Flying qualities

of air vehicles Volume 2 Proposed MIL handbookIAD-A123726] p 441 N83-25704

KLEMAN, BLaser safety of air bathymetry

IFOA-C-30292-E1] p 478 N83-27210KNAUS, A

A technique to determine lift and drag polars in flightp422 A8336913

KNOTTS, LIn-flight simulation at the U S Air Force and Naval Test

Pilot Schools[AIAA PAPER 83-1078] p 436 A83-36206

KNOX, C EDescription of the computations and pilot procedures

for planning fuel-conservative descents with a smallprogrammable calculator[NASA-TM-85642] p 444 N83-25707

KOEGEL, PDesign and development of a small gasturbme engine


KOENIG, GThe influence of defects on the operational strength

of disks and wheels in engines p 472 A83-33964KOPELEV, S Z

Profile losses during the release of air onto the surfaceof nozzle vanes p 418 A83-35590

KORN, J AAspects of the T56 power section usage/operating

costs[AIAA PAPER 83-1408] p 457 A83-36397

KORPPOO, S'Larus' and 'VP-1' tested in winter 1982

p485 A83-34859KOSUT, R L

Old problem/new solutions - Motion cuing algonthmsrevisitedI AIAA 83-1082] p 480 A83-36223

KOTSCHOTE, JWind tunnel tests of over-the-wing nacelles

p422 A83-36916KOTTAPALLI, S B R



KOU, Y MPrediction of stagnation flow heat transfer on


KRAVETS, V VSeparated flows on a concave conical wing

p418 A83-35707KREJSA, E A


KRESS, R WVariable sweep wing design

[AIAA PAPER 83-10511 p 438 A83-36461KRETSCHMER, D

The effects of fuel properties upon pollutants presentin gas turbine aero-engines p 469 A83-35813

KROTHAPALLI, AEdge tones in high-speed flows and their application

to multiple-let mixing p 482 A83-36077KROUTIL.J C

Response of a supersonic inlet to downstreamperturbations| AIAA PAPER 83-2017] p 422 A83-36403

KRUEGER, S PThe super stallion p 435 A83-36075

KRYS, N HExperimental testing of flying qualities theories

IAD-A124699] p 440 N83-25697KULCHIKHIN, E T

The use of a structural model for determining theadaptability curve for turbine disks in stress concentrationzones p 445 A83-35039

KUMAR, V AExpenmental investigation on the role of flexbars and

metallic end seals in squeeze film dampersp 473 A83-35862

KUZNETSOV, V MThe relationship between the aerodynamic and acoustic

characteristics of coaxial jets p 482 A83-35712KWON, O K

Prediction of stagnation flow heat transfer onturbomachmery airfoils[AIAA PAPER 83-1173] p 420 A83-36259

LAFRAMBOISE, J EThe Transportation Development Centre contribution to

air cushion technology p 486 A83-35059LAKSHMIKANTAN, K

Experimental investigation on the role of flexbars andmetallic end seals in squeeze film dampers

p 473 A83-35862LAKSHMINARAYANA, B

End wall flow characteristics and overall performanceof an axial flow compressor stageINASA-CR 3671 ] p 427 N83-26819

LAMAR, J ERecent studies at NASA-Langley of vortical flows


LAMBERT, MThe future of the manned aircraft p 416 A83-36960

LAMBERTY, B JMultimode planar spiral for OF applications

p 430 A83-35089LAMDEN, D I

The distnbution of the disperse fraction of a polydisperselet miected into a gas flow p 473 A83-34472

LANGRAND, AAISA - Program for automated treatment of aeronautical

data p462 A83-35598LARSEN, J M

Life prediction for turbine engine componentsp474 A83-36174

LASAGNA, P LIn-flight acoustic test results for the SR-2 and SR-3


LAVRUKHINA, M PThe relationship between the aerodynamic and acoustic

characteristics of coaxial lets p 482 A83-35712LAW, C H


LAW, R DEarly experience in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726LAW, W C

The remote link unit A demonstration of operationalperformance Part 3 Design manual, volume 1IAD-A124621] p 476 N83-25934



The remote link unit A demonstration of operationalperformance, part 1[AD-A124619] p 476 N83 25939

LEAVITT, L DEffect of empennage location on twin-engine

afterbody-nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2[NASA-TP2116] p424 N83-25666

LEE, W NNOVA-2S correlation with KC-135A fuselage shock tube


LEFEBVRE, A HFurther studies on the prediction of spray evaporation

rates p 468 A83 35811LEPICOVSKY, J

Aerodynamic measurements about a rotating propellerwith a laser velocimeter[AIAA PAPER 83-1354] p 421 A83 36355

LEUPP, 0 GACES II negative Gz restraint investigation

[AD-A124713] p 430 N83-25685LEVINE, D M


LEVITT, B B1983 LTA technology assessment

[AIAA PAPER 83-1617] p 437 A83-36406LEW, E A


p431 A83-35192LEWIS, G M

V/STOL status from the engine technology viewpointp458 A8336912

LEWIS, W JV/STOL status from the engine technology viewpoint

p458 A83-36912LIESNER, CH


LILLEY, D EExperimental studies of the separating confluent


LILLEY, D GThe performance of an annular vane swirler

[AIAA PAPER 83-1326] p 455 A83-36340LIU, T-M


LOECHELT, EMatenals in the mirror of aviation criteria

p 434 A83-33952LOH, N K

Microprocessor-based optimal controllers for ahelicopter turret control system p 434 A83-35138

LONDON, G G , JRInvestigation of an improved finite element model for a

repaired T-38 horizontal stabilizer flutter analysis usingNASTRAN(AD-A124741] p 461 N83-25717

LONG, W DHigh altitude |et fuel photochemistry

[AD-A125035] p471 N83 27035LONGAKER, R G

A new class ACV - Tanker freighterp485 A83-35053

LUCAS, J GLow flight speed acoustic results for a supersonic inlet

with auxiliary inlet doors[NASA-TM-83411) p 482 NB3-27794

LUDEMANN, S GProp-fan powered aircraft - An overview

[SAE PAPER 820957] p 434 A83-33629LYKOV, O P


p 468 A83-34500

MMACARTHUR, C D


MACH, K DA survey of trends in modern turbine technology

[AIAA PAPER 83-1174] p 451 A83-36260

B-6

PERSONAL AUTHOR INDEX NIELSON, C. E.

MACKALL, K Gtn-fhght acoustic test results (or the SR 2 and SR-3


MAGRE, PSemi implicit calculation method of the (low field in a

duct with the flame stabilized by a stepp446 A83-35820

MAHAPATRA, P RScanning strategies for next generation weather radars

A study based on lifetimes of convective atmosphericphenomena hazardous to aviation[FAA-RD-82-69] p 476 N83-25929

MAI, Z -FA dynamic model of turbojet in starting at high altitude

p 447 A83-35846MAINQUIST, R


MAITA, MOn the propulsion system of the NAL quiet STOL

research aircraft p 446 A83-35831MANNHEIMER, R J

Feasibility of a full-scale degrader for antimistmgkerosene[AIAA PAPER 83-1137] p 469 A83-36240

MANTEL, S J , JRMicroeconomic models for process development

p472 A83 33650MARCHAND, M

Evaluation of aerodynamic derivatives from Do 28-TNTfree-flight model tests[ESA-TT-784] p 442 N83-25706

MARCROFT, K MDesign for testing of a low altitude night in weather

attack system[AIAA PAPER 83-1061] p 432 A83 36470

MARKS, K EDevelopment and production cost estimating

relationships for aircraft turbine engines[AD-A123753] p 459 N83 25714

MARKS, M DPrototyping for fun and profit

[AIAA PAPER 83-1045] p415 A83 36458MARUTHI, V

Stress analysis of critical areas ol low-pressurecompressor-disc assembly of a developmentalaero-engine p 449 A83 35880

MASCOLA, RSingle- and multiple-crater induced nosetip transition

p 420 A83-36078MASIULANIEC, K C

Numerical simulation of electrothermal de-icingsystems[AIAA PAPER 83-0114] p 428 A83-36043

MASON, M LA static investigation of yaw vectoring concepts on

two-dimensional convergent divergent nozzles[AIAA PAPER 83-1288] p 421 A83-36324

MASQUELIER, M IApplication of the vortex-lattice method to propeller

performance analysis[AD-A124837] p 459 N83 26840

MATHIOUDAKIS, KFlow in rotating stall cells of a low speed axial flow

compressor p419 A83-35874MATSUKI, M


MATUK, CImpact damping and airplane towing

p428 A83-33625Flight tests of tow wire forces while flying a racetrack

pattern p 439 A83-36919MAYER, N J


MCAROLE, J GA compact inflow control device for simulating flight fan

noise[NASA-TM-83349] p 482 N83-26643

MCCAFFREY, G F WCanadian forces tracker aircraft full-scale fatigue test


MCDANIELS, D LEvaluation of low-cost aluminum composites for aircraft


MCFARLAND, R ESpectral decontamination of a real time helicopter

simulation[AIAA PAPER 83-1087) p 436 A83-36211

MCGUIRE, P DHigh Reynolds number tests of the CAST 10-2/DOA 2

airfoil in the Langley 0 3-meter transonic cryogenic tunnel,phase 1[NASA TM 84620] p 424 N83-25660

MCLAFFERTY, G HResults of tests of a rectangular vectoring/reversing

nozzle on an F100 engine[AIAA PAPER 83-1285] p 454 A83-36322

MCMANUS, K RImportance of inlet boundary conditions for numerical

simulation of combustor flows[AIAA PAPER 83-1263] p 454 A83-36314

MENGZI, CThe prediction of performance of turbojet engine with


MENTE, L JNOVA-2S correlation with KC-135A fuselage shock tube


MERCIER, O L.Interactive fine-tuning of linear-quadratic governers by


METZ, T RDevelopment of simulated mission endurance test

acceleration factors in determining engine componentserviceability and failure mode cnticality[AIAA PAPER 83-1409] p 457 A83-36398

MIGNOSI, AProblems involved by the instrumentation and the

conception of cryogenic tests p 465 N83-25725MIKHAILOV, F A


p460 A83-33900MILES, G


MILES, J HCross spectra between temperature and pressure in a


MINER, G AAircraft aerodynamic prediction method for V/STOL

transition including flow separation[NASA-CR-166467] p 426 N83-26818

MITCHELL, D GProposed MIL standard and handbook Flying qualities


MIURA, YPreliminary investigation on the performance of


MIYOSHI, TResidual life prediction for jet engine rotor disks at

elevated temperature p 472 A83-33974MONAGAN, S J


MONEY, K ETheory underlying the peripheral vision horizon device

[AD-A124426] p 445 N83-25710MONSER, G


MONTLE, L KLarge jet aircraft validation and demonstrations - An

overview of Boeing expenence[AIAA PAPER 83 1049] p 439 A83-36472

MOORE, W G , JRConcepts for a future joint airlift development program

[AIAA PAPER 83-1591] p 429 A83-36951MORAN, D 0

Dynamic modeling of an air cushion vehiclep 486 A83-35054

MOREIGNE, OInteractive fine tuning of linear-quadratic governers by


MORELLO, S AFlight management concepts development for fuel

conservation p 447 A83-35843MORITA, M


MORLEIGH, SComputer model of a collision-avoidance system for air

traffic control p 431 A83-35275

MOROZOV, V IIntegro-differential equations of the dynamics of elastic

systems in nonstationary flows p 474 A83-35933MOSES, H L

High angle-of-attack cascade measurements andanalysis p 419 A83-35875

MOSTINSKII, I LThe distribution of the disperse fraction of a polydisperse

jet injected into a gas flow p 473 A83-34472MOUNT, J S


MOXON, JAR 318 - Italy's low-cost GA turboprop

p 445 A83-35675MOYNIHAN, M E


MRAZEK, J E,JRA complete introduction to the revolutionary new way

to fly ultralights p 415 A83-33622MRAZEK, J E , SR

A complete introduction to the revolutionary new wayto fly ultralights p 415 A83 33622

MULARZ, E JNew trends in combustion research for gas turbine

engines p 446 A83 35806MULCARE, D

Digital flight control system validation[AD-A124506] p 462 N83 26847

MUNIN.A GThe relationship between the aerodynamic and acoustic

characteristics of coaxial jets p 482 A83 35712MUNTASSER, M A


MURTHY, S N BEffect of humidity on jet engine axial-flow compressor

performance p 448 A83-35856

NNAGANO, S


NAGARAJA, K SA collection of papers in the aerospace sciences

[AD-A122667] p 417 N83-26787Advances in ejector technology A tribute to Hans von

Oham's vision p 477 N83-26805Statistical experimental designs in computer aided

optimal aircraft design p 442 N83-26812NAGEL, D C

The man-vehicle systems research facility - A new NASAaeronautical R & D facility[AIAA PAPER 83-1098] p 463 A83-36218

NAPORA, ESome applications of ultrasonic methods for the quality

control of nonmetallic objects p 475 A83-36794NASSAR, M H

The effect of variation of diffuser design on theperformance of centrifugal compressors

p 448 A83-35866NECKAR, F


NELSON, D PEjector nozzle test results at simulated flight conditions

for an advanced supersonic transport propulsion system[AIAA PAPER 83-1287] p 454 A83-36323


NEUMANN, H EDynamic distortion in a short s-shaped subsonic diffuser

with flow separation[NASA-TM-84312] p 459 N83-26C38

NEWMAN, J SA survey of helicopter and ambient urban noise levels


NGUYEN, L TPilot human factors in stall/spin accidents of supersonic

fighter aircraft[NASA-TM-84348] p 462 N83-26846

NICHOLAS, TLife prediction for turbine engine components

p474 A83-36174NIELSON, C E


B-7

NIJI, K. K. PERSONAL AUTHOR INDEX

NIJI, K KUltrasonic weld bonding of helicopter primary

structures(AD-A124645] p 477 N83-26081

NORBUT, T JDevelopment of a turbojet engine simulator for scale



NORTH, D MCF34 upgrades Challenger capabilities

p434 A83-35315NOVICK, A S

Advanced preplan engine characteristics andtechnology needs[AIAA PAPER 83-1155] p 450 A83-36250

NUGENT, JPressures measured in flight on the aft fuselage and

external nozzle of a twm-|et fighter[ NASA TP 2017 ] p 424 N83-25665

OBARA, C JNatural laminar flow data from full-scale flight and

wind-tunnel experiments p 422 A83-36409OBIKANE, Y


OBRIEN, W FHigh angle-of-attack cascade measurements and

analysis p419 A83-35875OCONNOR, C M


ODGERS, JThe effects of fuel properties upon pollutants present

in gas turbine aero-engines p 469 A83-35813OHNABE, H


ONEILL, J PA placement model for flight simulators

[AD-A123782] p 466 N83-25730ORAKOVA, I E

The effect of products baêd on higher fatty acids onthe performance characteristics of jet fuels

p 468 A83-34500ORLINO, D G

Evaluation of the effect of voids in composite main rotorblades p 472 A83-33507

Evaluation of the effect of voids in composite main rotorblades p 435 A83-35950

ORZECHOWSKI, J AAn assessment of factors affecting prediction of


OTTOMEYER, J DAirworthiness and flight characteristics test Part 2


OWENS, C AFlight operations A study of flight deck management

p 428 A83-33767

PADMANABHAN, RStress analysis of critical areas of low-pressure


PAK, E GThe Ka-26 helicopter p 437 A83-36448

PANHUISE, V ENondestructive evaluation methods for implementation

of damage-tolerant designed gas turbine enginecomponents[AIAA PAPER 83-1232] p 452 A83-36295

PAPAILIOU, K DA contnbution to the calculation of secondary flows in

an axial flow compressor p 419 A83-35852PARRAG, M

In-flight simulation at the U S Air Force and Naval TestPilot Schools[AIAA PAPER 83-1078] p 436 A83 36206

PASE, R LDesign and performance of a low aspect ratio, high tip

speed multi-stage compressor[AIAA PAPER 83-1161] p 451 A83-36253

PAUL, W FAll weather heliports and airway system - The future

need p 463 A83-36073PAULSON, J W.JR


PAYEN, J MContainment of turbine engine fan blades

p449 A83-35871PEDUZZI, A


PELEPEICHENKO, I PMethod of studying the operating temperature of gas

turbines[PNR-90159) p460 N83-26842

PELLERIN, C JDetermination of the sensitivity of U S Air Force aircraft


PETERSON, J L.Results of tests of a rectangular vectoring/reversing

nozzle on an F100 engine[AIAA PAPER 83-1285] p 454 A83-36322

PETITNIOT, J LMaterials and modelling technology for cryogenic

environment p 465 N83-25723PETROV, B N


p 460 A83-33900PETTY, J S

A collection of papers m the aerospace sciences[AD-A122667] p417 N83-26787

PFEIL, 0 UAirframe RDT&E cost estimating A justification for and

development of unique cost estimating relationshipsaccording to aircraft type[AD-A123848] p 417 N83-25656

PFLUG.D RComposite material aircraft electromagnetic properties

and design guidelines[AD-A124016) p 470 N83-25795

PICASSO, B D , IIIAirworthiness and flight characteristics test Part 2


PIERCE, G AHelicopter rotor loads using discrelized matched


Helicopter rotor loads using matched asymptoticexpansions User's manual[ N AS A-CR-166093] p 423 N83-25659

PINSLEY, E AAdvanced techniques for gas and metal temperature

measurements in gas turbine engines[AIAA PAPER 83-1291 ] p 444 A83-36325

PITTS, J N,JRHigh altitude jet fuel photochemistry

[AD-A125035] p 471 N83-27035PLANT, T J


PLOKHIKH, V PA small parameter method in problems of maneuvering


PLOURDE, G AFighter engine cycle selection

[AIAA PAPER 83-1300] p 457 A83-36412POKHVALENSKII, V L


p460 A83-33900POLLAK, R R

Cntena for optimizing starting cycles for highperformance fighter engines[AIAA PAPER 83-1127] p 450 A83-36236

PONOMAREV, A TIntegro-differential equations of the dynamics of elastic

systems in nonstationary flows p 474 A83-35933POOLE, W E

Eccentric end wear in cylindrical roller beanngs can bepredicted and prevented[AIAA PAPER 83-1132] p 474 A83-36237

POVINELLI, LThree-dimensional compressible viscous analysis of

mixer nozzles[AIAA PAPER 83 1401 ] p 422 A83-36391

PRELL, M EEffects of compressor hub treatment on stator stall


PRICE, H J.JRWind tunnel investigation of varying hinged flaps

[AD-A124703] p 424 N83-25668

QQIUTING, D


p 446 A83-35832

RAGHUNATH, B JStress analysis of critical areas of low-pressure


RAM, R BStatistical experimental designs in computer aided

optimal aircraft design p 442 N83-26812RAMACHANDRA, K


RAMACHANDRA, S MThe transient performance of turbojet engines and axial

compressors p 447 A83-35847RANSOM, S


RAO, G VNonlinear supersonic flutter of panels considering shear

deformation and rotary inertia p 473 A83-34315RAO, J S


RAO, K SNonlinear supersonic flutter of panels considering shear

deformation and rotary inertia p 473 A83-34315RAVIGNANI, G L.

Microeconomic models for process developmentp 472 A83-33650

RAY, D JModern technology and airborne engine vibration


RAY, E JHigh Reynolds number tests of the CAST 10-2/DOA 2

airfoil in the Langley 0 3-meter transonic cryogenic tunnel,phase 1[NASATM-84620] p 424 N83-25660

REED, J EDigital flight control system validation

[AD-A124506] p 462 N83-26847REED, R J

LCC evaluation of advanced engine damage tolerancegoals for a hot-section disk[AIAA PAPER 83-1407] p 456 A83-36396

REESE, B AGround simulation of engine operation at altitude

p 463 A83-35863REEVES, B

Single- and multiple-crater induced nosetip transitionp420 A83-36078

REID, M DSurvivability of interdiction aircraft Sensitivity to terrain

following, command altitude, velocity and electroniccounter measures[AD-A124870] p 443 N83-26B33

REIDER, S BEffect of fuel composition on Navy aircraft engine hot

section components[AIAA PAPER 83-1147] p 450 A83-36244

RENARD, AOmega application in the Indonesian region

p 431 A83-35599REPIK, E U

Optimum wire screens for control of turbulence in windtunnels p 417 A83-33772

REUBUSH, D EEffects of varying podded nacelle-nozzle installations

on transonic aeropropulsive characteristics of a supersonicfighter aircraft[NASA-TP-2120] p 427 N83-26821

RIAZ, AInvestigation of a third order baro damped verticle

channel of INS[AD-A124882] p 432 N83-26828

B-8

PERSONAL AUTHOR INDEX SPADACCINI, L. J.

RICHARDS, C JThrust reverser exhaust plume Reingestion tests (or a

STOL fighter model(AIAA PAPER 83-1229] P 452 A83-36293

RICHE, K AAnalysis of F 16 radar discrepancies

[AD-A124749] P 476 N83-25948RICKETTS, R H

Some recent applications of XTRAN3S[NASA-TM-85641] P 426 N83-26815

RIODER, S OExperimental study of strength and existance domain

of ground to-air inlet vortices by ground board staticpressure measurements[PB83-144865) P 460 N83-26843

RIDDLE, D WApplications of advanced upper surface blowing

propulsive-lift technology[SAE PAPER 820956] P 433 A83 33628

RIGGS, G EAnalysis of progressive collapse of complex structures

[AD-A125266] P 478 N83-27260RILEY, W J

Phase 2A bench model development tactical rubidiumfrequency standard[AD-A124462] P 477 N83-25990

RODGERS, CThe performance of single shaft gas turbine load

compressor auxiliary power units[AIAA PAPER 83-1159] P 451 A83-36251

ROGERSON, D BXB-70 technology advancements

[AIAA PAPER 83-1048] P 437 A83-36460ROLSTON, D R

Sinusoidal integration for simulation of second-ordersystems[AIAA PAPER 83-1086] P 480 A83 36210

ROSENTHAL, GThe application ol low-cost demonstrators (or

advancead fighter technology evaluation[AIAA PAPER 83-1052] P 438 A83-36462

ROSKAM, JAnalysis of nonplanar wing-tip-mounted lifting surfaces

on low-speed airplanes[NASA-CR-3684] P 424 N83-25667

ROSS, J WXB-70 technology advancements

[AIAA PAPER 83-1048] P 437 A83-36460ROWE, W T

Technology status for an advanced supersonictransport[SAE PAPER 820955] P 433 A83 33627

RUSAK, ZNumencal calculation of nonlinear aerodynamics of

wing-body configurations P 420 A83 36076RYSEV, O V

The motion dynamics of parachute systemsp 422 A83-36450

SACCULLO, AExperimental study of main rotor/tail rotor/airframe

interactions in hover Volume 1 Text and figures[NASA-CR 166485] P 427 N83-26820

SAHINKAYA, M NA modified algorithm for determining structural

controllability P 480 A83-36455SAJBEN, M

Response of a supersonic inlet to downstreamperturbations[AIAA PAPER 83-2017] P 422 A83-36403

SAMUELSSON, IExperimental study of strength and existance domain

of ground-to-air inlet vortices by ground board staticpressure measurements[PB83-144865] P 460 N83 26843

SANDER, G FThe performance of an annular vane swirler

[AIAA PAPER 83-1326) P 455 A83 36340SANTANGELO, T C


SARGENT, JLACV-30 supportability P 486 A83-35062

SAROHIA, VEntrainment and mixing in thrust augmenting electors

[AIAA PAPER 83-0172] p419 A83-36046SASAKI, M


SASHEVSKII, V VThe effect of products based on higher fatty acids on

the performance characteristics of jet fuelsp 468 A83-34500

SAVAGE, R TClimatic laboratory survey Hughes YAH-64 helicopter

[AD-A124670] p 440 N83-25698SCAFETTA, D A

Simulator fidelity and flight test data - Improving the flightperformance ol the B-52H WST production unit flightstation simulator(AIAA PAPER 83-1075) p 436 A83-36204

SCHETZ, J AInjection, atomtzation, ignition and combustion of liquid


SCHMITZ, F HFull-scale measurements of blade-vortex interaction

noise p 482 A83-33505Full-scale measurements of blade-vortex interaction

noise p 435 A83-35947SCHNEIDER, J J

The history of V/STOL aircraft p 435 A83 36074SCHRECK, K

Material, structural component, service lifep 468 A83-33953

SCHWARMANN, L.On improving the fatigue performance of a double-shear

lap |0int p 473 A83-34744SCHWARTZ, A C

U S sets own standards for airport lightingp 463 A83-35625

SCHWEITZER, J KMaximum loading capability of axial flow compressors

[AIAA PAPER 83-1163] p 451 A83-36254SCHWENK, J C


SEARS, W RA note on adaptive wind tunnels with imperfect control

p466 N83-26792SEDOON, J

The swirl in an S-duct of typical air intake proportionsp418 A83-35620

SEGINER, ANumerical calculation of nonlinear aerodynamics of

wing-body configurations p 420 A83-36076SEIDEL, D A


SELEGAN, D RAerospace technology demonstrators/research and

operational options(AIAA PAPER 63 1054) p 438 A83-36465

SEWALL, T RThe impact of engine usage on life cycle cost

[AIAA PAPER 83 1406] p 456 A83-36395SEYB, N J


SHAPIRO, E YApplication of maximum likelihood estimation to the


SHASHKINA, G NCalculation of subsonic flow past rectangular wings and


SHASTRI, RAnalysis of a real-time application

[AIAA PAPER 83-1088] p 480 A83-36212SHAVER, B E

Canadian forces tracker aircraft full-scale fatigue testat the national aeronautical establishment

p 433 A83-33548SHEA, J F

Concepts for a future joint airlifl development program[AIAA PAPER 83-1591] p 429 A83-36951

SHEEHY, T WExperimental study of main rotor/tail rotor/airframe


SHELTON, W I,JRFlutter prediction in forward-swept wings by assumed

modes and strip theory[AD-A124715] p 461 N83-25719

SHINER, R JThe man-vehicle systems research facility - A new NASA


SHUFORD, R JEvaluation of the effect of voids in composite main rotor


blades p 435 A83-35950SHVETS, A I

Separated flows on a concave conical wingp418 A83-35707

SIDANA, M LComponent life reduction due to use of AVGAS in gas

turbine engines p 449 A83-35869SIDDONS, W D , JR

PANAIR Pilot Code application to subsonic nacelle typeinterior flows[AIAA PAPER 83 1369] p 421 A83-36365

SIEGELMAN, DSingle- and multiple-crater induced nosetip transition

p 420 A83-36078SIGNORELLI, R A


SIMPSON, C HAdvanced navigation systems and fuel conservation

p 428 A83-33545SIMPSON, D L

Canadian forces tracker aircraft full scale fatigue testat the national aeronautical establishment

p 433 A83-33548SIMS, R E

Fighter engine cycle selection(AIAA PAPER 83-1300) p 457 A83-36412

SINACORI, J BResearch and analysis of head-directed area-of-mterest


SINGH, GThermal cycling in compact plate-fin heat exchangers

p 445 A83-34253SINSKY, A I


p431 A8335192SIT ARAM, N


SKONING, G DAirline safety and labor relations law - Balancing rights

and responsibility p 484 A83-34475SMETANA, D


SMITH, HPerformance flight testing p 433 A83-33621

SMITH, N KThermodynamics of organic compounds

I AD-A125022] p 483 N83-27895SMITH, R E


SMITHER, M AThe remote link unit A demonstration of operational





SNYDER, C E,JRDetermination of the sensitivity of U S Air Force aircraft


SOBEL, K MApplication of maximum likelihood estimation to the


SOLOMON, RFeasibility of dry lubrication for limited-duty gas turbine


SONIN, V VA small parameter method in problems of maneuvering

space vehicles with aerodynamic efficiencyp467 A83-34849

SORENSEN, J AFlight management concepts development for fuel

conservation p 447 A83-35843SOSEDKO, IU P

Optimum wire screens for control of turbulence in windtunnels p 417 A83-33772

SPACHT, GX-29 integrated technology demonstrator and ATF

[AIAA PAPER 83-1058] p 438 A83-36469SPADACCINI, L. J


B-9

SPEARMAN, M L PERSONAL AUTHOR INDEX

SPEARMAN, M LSome historical trends in the research and development

of aircraft[NASA-TM-84665] p417 N83-26785

SPRINKEL, D MWind tunnel test of a C-18 aircraft modified with the

advanced range instrumentation aircraft radomeIADA124771] p 425 N83-25671

SRINIVASA, KComponent life reduction due to use of AVGAS in gas

turbine engines p 449 A83-35869SRINIVASAN, R

Experiments in dilution jet mixing(AIAA PAPER 83 1201] p 475 A83-36277

SRIRANGARAJAN, H RThe response of aircraft to pulse excitation

p434 A83-34312ST LAURENT, R

A design synthesis model for ACV/SES lift systemsp 486 A83-35057

STANCIU, VGeneralization of the air-|et propulsion systems, the 'N'

flow turbo-jet engine[AD-A123932] p 459 N83-25715

STANEWSKY, EHigh Reynolds number tests of the CAST 10-2/DOA 2

airfoil in the Langley 0 3-meter transonic cryogenic tunnel,phase 1INASA-TM-84620] p 424 N83-25660

STANKIEWICZ, EForced and self-excited vibrations of gas-turbine

assemblies with perfect and perturbed symmetryp 458 A83-36791

STATECNY, JA contribution to airworthiness certification of gas turbine

disks p 449 A83-35872STAVINOHA, L I

Emergency fuels technologyIAD-A125275] p 471 N83-25904

STEFANESCU, D MPreliminary science report on the directional solidification

of hypereutectic cast iron during KC-135 low-GmaneuversINASA-TM-82528] p 470 N83-25854

STEIN, T ADevelopment trends in engine durability

[AIAA PAPER 83-1297] p 455 A83-36329STEINER, J E

Large |et aircraft validation and demonstrations - Anoverview of Boeing experience[AIAA PAPER 83 1049] p 439 A83-36472

STENBERG, K VYAV-8B flight demonstration program

[AIAA PAPER 83-1055] p 438 A83-36466STETSON, H D


STEVENS, G W HNet-skirt addition to a parachute canopy to prevent

inversion p 428 A83-36911STONIK, O G

The distribution of the disperse traction of a polydispersejet injected into a gas flow p 473 A83-34472

STOWELL, W RApplication of thin film strain gages and thermocouples


STRAIGHT, D MThrust performance of a variable-geometry, divergent

exhaust nozzle on a turbojet engine at attitudeINASA-TP-2171] p459 N83-26839

STUFFLEBEAM, J HCARS temperature and species measurements in


STULL, F DCoaxial dump combustor investigations

p459 N83-26791STUMPF, R

Dynamic distortion in a short s-shaped subsonic diffuserwith flow separation[NASA-TM-84312] p 459 N83-26838

STUBGESS, G JImportance of inlet boundary conditions for numerical


SULLIVAN, P AApplication of system identification flight analysis


SULLIVAN, R EApplication of 3D aerodynamic/combustion model to


SULLIVAN, T JThe aerodynamic design and performance of the

General Electric/NASA EEE fan[AIAA PAPER 83-1160] p 451 A83-36252

SURIKOV, N FThe Ka-26 helicopter p 437 A83-36448

SUSSMAN, M BSTOL wind tunnel test results for a tactical


SUTTON, RApplication of 3D aerodynamic/combustion model to

combustor primary zone study(AIAA PAPER 83-1265] p 454 A83-36316

SYED, S AImportance of inlet boundary conditions for numerical


SZACHNOWSKI, WSome applications of ultrasonic methods for the quality

control of nonmetallic objects p 475 A83-36794SZCZEPANSKI, K


SZETELA, E JThermal stability of alternative aircraft fuels

[AIAA PAPER 83-1143) p 470 A83-36243SZODRUCH, J

Wind tunnel tests of over-the-wmg nacellesp 422 A83-36916

TABAKOFF, WHigh temperature erosion study of INCO 600 metal

P468 A83-35247Effect of sand erosion on the performance deterioration


TAILLON, N VPressures measured in flight on the aft fuselage and


TAKASAWA, KOn the propulsion system of the NAL quiet STOL

research aircraft p 446 A83-35831TAN, C S


TAVORA, C JThe remote link unit A demonstration of operational



The remote link unit A demonstration of operationalperformance Part 2 User s manual[AD-A124620] p 476 N83-25938


TELLEX, P ACARS temperature and species measurements in


TEREN, FNASA propulsion controls research

[NASA-TM-83343] p 458 N83-25711TESCH, W A

Design and performance of a low aspect ratio, high tipspeed multi-stage compressor[AIAA PAPER 83-1161 ] p 451 A83-36253

TETLOW, RLight aircraft and sailplane structures in reinforced

plastics p 435 A83 36065TEVELDE, J


THOMAS, LHigh-gain error actuated flight control systems for

continuous linear multivanable plants[ AD-A124871 ] p 462 N83-26848

THOMASON, S BHigh angle-of-attack cascade measurements and

analysis p419 A83-35875TIKHANINA, I G


TINOCO, E NPAN AIR applications to aero-propulsion integration

[AIAA PAPER 83-1368] p 421 A83-36364

TIPNIS, V AMicroeconomic models for process development

p472 A83 33650TJONNELAND, E

Inlet engine, airframe controls integration developmentfor supercruising aircraft p 447 A83-35842

TODISCO, ASingle- and multiple-crater induced nosetip transition

p 420 A83-36078TORAL, H

Temperature and composition measurements in aresearch gas turbine combustion chamber

p445 A83-35790TORENBEEK, E

Generalized maximum specific range performancep439 A83-36918

TORISAKI, TOn the propulsion system of the NAL quiet STOL

research aircraft p 446 A83-35831TREMILLS, J A

A design synthesis model for ACV/SES lift systemsp486 A83-35057

TRIPPI, AA study of the response of a turbojet engine to the inlet

temperature transients p 448 A83-35849TSUCHIYA, T

Effect of humidity on jet engine axial flow compressorperformance p 448 A83-35856

TURNER, E RPrediction of stagnation flow heat transfer on

turbomachinery airfoils(AIAA PAPER 83-1173] p 420 A83-36259

VAGNER, E TLasers in aircraft construction p 472 A83-34170

VAIDYANATHAN, A RHelicopter rotor loads using discretized matched


Helicopter rotor loads using matched asymptoticexpansions User's manual[ N AS A-CR-166093] p 423 N83-25659

VAN DEN BROEK, G JCorrection to the wing source velocity error in

Woodward's USSAERO code p 423 A83-36920VANBUSSEL, G J W

Aerodynamic research on Tipvane wmdturbmes[PB83-147413] p 479 N83-27476

VANDAM, C PAnalysis of nonplanar wing-tip-mounted lifting surfaces


VANEK, VContribution to centrifugal compresor impeller design

p 448 A83-35865VANHOLTEN, T


VANKUIK, G A MAerodynamic research on Tipvane wmdturbmes

[PB83 147413] p 479 N83-27476VELKOFF, H R


VENKATRAYULU, NEffect of entry boundary layer thickness on secondary


VERGA, R LAir Force technical objective document FY 1984

[AD-A123961] p 487 N83-26783VICROY, D D

Descnption of the computations and pilot proceduresfor planning fuel-conservative descents with a smallprogrammable calculator[NASA TM-85642] p 444 N83-25707

VIKTOROV, B VUsing adaptive control to synthesize invariant and

partially autonomous automatic stabilization systemsp 460 A83-33900

VISHNIAKOVA, T PThe effect of products based on higher fatty acids on

the performance characteristics of jet fuelsp468 A83-34500

VITTAL, B V RHigh temperature erosion study of INCO 600 metal

p 468 A83-35247VIZZINI, R W

Integrated propulsion-aircraft control evaluation for acurrent Navy fighter[AIAA PAPER 83-1236] p 453 A83-36299

B-10

PERSONAL AUTHOR INDEX ZRNIC, D S.

VOGEL, R EEffect of fuel composition on Navy aircraft engine hot

section components(AIAA PAPER 83-1147] p 450 A83-36244

VONPRAGENAU, G L.Damping seal for turbomachmery

[NASA-CASE-MFS-25842-1] p 477 N83-26080VOROBEV, N F

Calculation of subsonic flow past rectangular wings andtheir combinations on the basis of a discrete vortexscheme p418 A83-35541

VOSTATEK, PInvestigation methods on residual stresses in aero

engines components p 449 A83-35879

wWAOOOUPS, M E


WADIA, A RNumerical calculations of time dependent

three-dimensional viscous flows in a blade passage withtip clearance[AIAA PAPER 83-1171] p 420 A83-36258

WAGENKNECHT, C DDevelopment of a turbojet engine simulator for scale


Performance capability of a Compact MultimissionAircraft Propulsion Simulator[AIAA PAPER 83-1358] P 464 A83-36356

WALKER, A CCanadian forces tracker aircraft full-scale fatigue test


WALLENBERG, R AComposite material aircraft electromagnetic properties

and design guidelines[AD-A124016] P470 N83-25795

WALLW, ASimulation program of rotary wings

[FOA-C-30308-E1] p 443 N83-26836WANG, J -H

Experimental research of the mechanism of flamestabilization in two phase mixture p 469 A83-35822

WARWICK, GGE's APG-67 - Fighter radar with a future

P432 A83-36625WASSERBAUER, C A


JT150 1/2-scale nozzle jet noise experiment andcomparison with prediction[NASA-TM-83370] p 482 N83-27793

WASSERSTROM, ENumerical calculation of nonlinear aerodynamics of

wing-body configurations p 420 A83-36076WATWE, U

Microeconomic models for process developmentp472 A83-33650

WEAVER, P MA wind tunnel study of the effects of a close-coupled

canard on the aerodynamic characteristics of aforward-swept wing in incompressible flow[AD-A124722] p 425 N83-25673

WEBB, JDigital flight control system validation

[AD-A124506] p 462 N83-26847WEDEKING, G


WEEKS, R AError sources in hybrid computer based flight


Real time simulation of mission environments foravionics systems integration[AIAA PAPER 83-1097] p 463 A83-36217

WEILKE, JStructural members made of high-strength cast

aluminum and their properties p 468 A83-33954WEISE, R A


WEISS, JUse of flight test results to improve the flying qualities

simulation of the B-52H weapon system trainer[AIAA PAPER 83-1091] p 437 A83-36215

WELLER, W HCorrelation and evaluation of inplane stability

characteristics for an advanced bearmgless mam rotor[NASA-CR-166448] p 440 N83-25695

WENNERSTROM, A JExperimental study of a high-through-flow transonic axial

compressor stage p419 A83-35853The use of vortex generators as inexpensive compressor

casing treatment p 459 N83-26798WESTRA, 0 P

Simulator design features for carrier landing Part 2In-simulator transfer of training[AD-A124024] p 466 N83-25733

WHEELER, R L.AP 1 -88 craft 001 prototype clearance trials

p485 A83-34862WHIPKEY, R R

Experimental studies of the separating confluentboundary-layer Volume 1 Summary[NASA CR 3655] p 427 N83-26822

WHITE, J LProgress in propulsion system/airframe structural


WHITE, M f.Applications of computational techniques in the design

of ramjet engines p418 A83-35828WHITE, M L

A tubular braided composite mam rotor blade sparp 435 A83-35949

WILFERT, M EGuidance control systems for aircraft on airport


WILKINSON, GForeign Technology Alert - Bibliography Transportation

safety[PB83-101659] p430 N83-25686

WILLIAMS, D P.Canadian forces tracker aircraft full-scale fatigue test


WILLIAMS, W JStatistical review of counting accelerometer data for

Navy and Marine fleet aircraft[AO-A124966I p 443 N83-26834

WILLIS, J BPrograms for the transonic wind tunnel data processing

installation Part 10 Six component measurementsupdated[AD-A122248] p 427 N83-26824

WILLIS, W SThe impact of engine usage on life cycle cost

[AIAA PAPER 83-1406] p 456 A83-36395WINER, A M

High altitude |et fuel photochemistry[ADA125035] p 471 N83-27035

WITCOFSKI, R 0Space-station crew-safety requirements

p467 A83-36408WITTENBERG, H

Generalized maximum specific range performancep439 A83-36918

WOO, Y KTransient heat-transfer measurement technique in wind


WOOD, J RNASA low speed centrifugal compressor for


NASA low speed centrifugal compressor forfundamental research[NASA-TM 83398] p 424 N83-25662

WOOD, N L.Development of an oculometer data collection

subsystem[AD-A124700] p 481 N83-26501

WOODWARD, D E1983 LTA technology assessment

[AIAA PAPER 83-1617] p 437 A83-36406WOODWARD, R P


WORTMANN, JThe influence of defects on the operational strength

of disks and wheels in engines p 472 A83-33964

YAN, D -YA dynamic model of turbojet in starting at high altitude

P447 A83-35846YANTIS, T F

Progress in propulsion system/airframe structuralintegration[AIAA PAPER 83-1123] p 437 A83-36234

YIP, L PNatural laminar flow data from full-scale flight and

wmd-tunnet experiments p 422 A83 36409YOCUM, A M

High angle-of-attack cascade measurements andanalysis p 419 A83-35875

YOKOI, SVariation of rotor blade vibration due to interaction of

inlet and outlet distortion p 450 A83-35882YOUNG, D E


p 431 A83-35090YOUNG, E


YOUNG, P HAdvanced propulsion controls - A total system view

p457 A83-36612YOUTH, S

Applications of advanced upper surface blowingpropulsive-lift technology(SAE PAPER 820956] p 433 A83-33628

ZABIEREK, D WA survey of trends in modern turbine technology

[AIAA PAPER 83-1174] p 451 A83-36260ZAKO, M


ZEISSER, M HA JT8D low emissions combustor by radial zoning

[AIAA PAPER 83-1324] p 455 A83-36339ZEITUNIAN, R KH

The aerodynamics of hyposonic velocities (On flows withlow Mach numbers) p417 A83-35535

ZEMSKAIA, A SOptimum wire screens for control of turbulence in wind

tunnels p417 A83-33772ZERNOV, I A

Aircraft production technology (2nd revised and enlargededition) p415 A83-36443

ZHANG, X NA study of lean extinction limit for pilot flame holder

p 469 A83-35821ZHANG, Y -M

Statistical study of TBO and estimation of accelerationfactors of ASMT for aircraft turbo-engine

p 448 A83-35858ZIKEEV, V V

Profile losses during the release of air onto the surfaceof nozzle vanes p418 A83-35590

ZIMENKOV, V DAn algorithm of flight simulation on a dynamic stand of

support type p 462 A83-34429ZIMMERMAN, P J

Development of simulated mission endurance testacceleration factors in determining engine componentserviceability and failure mode cnticahty[AIAA PAPER 83-1409] p 457 A83-36398

ZRNIC, D SScanning strategies for next generation weather radars

A study based on lifetimes of convective atmosphericphenomena hazardous to aviation[FAARD-82-69] p 476 N83-25929

B-11

CORPORATE SOURCE INDEX


Typical Corporate SourceIndex Listing

Anacapa Sciences, Inc, Santa Barbara, Calif— Importance of topographic features and tacticalannotations on maps used by Army aviators fornap-of-the-earth flight[AO-A118101] p28 N83-11107

ITITLE

REPORTNUMBER

I

PAGENUMBER

NASAACCESSION

NUMBER

Listings in this index are arranged alphabetically bycorporate source The title o1 the document is usedto provide a brief descnption of the subject matterThe page number and the accession number areincluded in each entry to assist the user in locatingthe abstract in the abstract section If applicable, areport number is also included as an aid inidentifying the document

Advisory Group for Aerospace Research andDevelopment, Neuilly-Sur-Seme (France)



Aeronautical Research Labs, Melbourne (Australia)Resonance tests on the tail of a CT4 aircraft

[AD-A124566] p 441 N83-25703Programs for the transonic wind tunnel data processing

installation Part 10 Six component measurementsupdated[AD-A122248] p 427 N83-26824

Air Force Aero Propulsion Lab , Wright-Patterson AFB,Ohio

Coaxial dump combustor investigationsp459 N83-26791


Air Force Flight Dynamics Lab, Wright-Patterson AFB,Ohio

Aircraft equipment random vibration test cntena basedon vibrations induced by turbulent airflow across aircraftexternal surfaces[AD-A123281] p 440 N83-25696

Advances in ejector technology A tribute to Hans vonOham's vision p 477 N83-26805


Air Force Geophysics Lab , Hanscom AFB, MassAnalysis and specification of slant wind shear

[AD-A125883] p 479 N83-26367Air Force Inst of Tech, Wright-Patterson AFB, Ohio

The effects of the Production Oriented MaintenanceOrganization (POMO) concept on ADTAC aircraftmaintenance productivity and quality[AD-A123981] p 416 N83-25655

Airframe RDTSE cost estimating A (ustification for anddevelopment of unique cost estimating relationshipsaccording to aircraft type1AD-A123848] P417 N83-25656

Wind tunnel investigation of varying hinged flaps| AD A124703] p 424 N83-25668

Transient heat-transfer measurement technique in windtunnel and data analysis technique using systemidentification theory[AD-A1246631 p 424 N83-25669


Wind tunnel test of a C-18 aircraft modified with theadvanced range instrumentation aircraft radome[AD-A124771] p425 N83-25671


Application ot a finite difference method to the transonicairfoil problem[AD-A124720] p 425 N83-25674

ACES II negative Gz restraint investigation[AO-A124713] 0430 N83-25685

Experimental testing of flying qualities theories[AD-At24699] p 440 N83-25697

An expenmental/analytical investigation into theperformance of a 20-percent thick, 8 5-percent cambered,circulation controlled airfoil[AD-A124732] p 441 N83-25701

Design and analysis of a subcntical airfoil for highaltitude, long endurance missions[AD-A124757] p 441 N83-25702

Modeling the helmet mounted sight system[AD-A124681 ] p 444 N83-25709





Generating an out-the-window cockpit image with thelAPX 432[AD-A124852] p 466 N83-25735






A review and companson of lightning return strokemodels using expenmental data[AD-A124680] p 479 N83-26345

Development of an oculometer data collectionsubsystem[AD-A124700] p 481 N83-26501


Computation of incompressible potential flow over anairfoil using a high order aerodynamic panel method basedon circular arc panels(AD-A124896] p 428 N83-26825

Investigation of a third order baro-damped verticlechannel of INS[AD-A124882] p 432 NB3-26B28

Dynamic charactenstics of aerial refueling systems(AD-A124770] p 442 N83-26830

Survivability of interdiction aircraft Sensitivity to terrainfollowing, command altitude, velocity and electroniccounter measures(AD-A124870] p 443 N83-26833

Application of the vortex-lattice method to propellerperformance analysis(AD-A124837) p 459 N83-26840

High-gam error actuated flight control systems forcontinuous linear multivanable plants[AD-A124871] p 462 N83-26848

Analysis of progressive collapse of complex structures1AD-A125266] p 478 N83-27260

Air Force Systems Command, Wright-Patterson AFB,Ohio

Generalization of the air-|et propulsion systems, the 'N'flow turbo-jet engine[ADA123932] p 459 N83-25715

Air Force Wright Aeronautical Labs, Wright-PattersonAFB, Ohio

Air Force technical objective document FY 1984[AD-A123961] p 487 N83-26783

A collection of papers in the aerospace sciences(AD-A122667) p417 N83-26787

Experimental analysis of the performance of an annularperipheral jet vehicle in ground effect(AD-A124949) p 443 N83-26832 I

Analytical Mechanics Associates, Inc, Mountain View,Calif

Flight management concepts development for fuel Iconservation p 447 A83-35843 [

Arizona Unlv, TucsonA note on adaptive wind tunnels with imperfect control

p 466 N83-26792 |Army Aviation Engineering Flight Activity, Edwards

AFB, CalifClimatic laboratory survey Hughes YAH-64 helicopter I

[AD-A124670] p 440 N83-25698 |Airworthiness and flight charactenstics test Part 2

YAH-64 advanced attack helicopter[AD-A125270] p 442 N83-25705 |

Army Propulsion Lab, Cleveland, OhioNew trends in combustion research for gas turbine

engines p 446 A83-35806Army Research and Technology Labs, Fort Eustis, Va


Army Research and Technology Labs, Moffett Field,Calif


Atlantic Research Corp, Alexandria, VaComposite material aircraft electromagnetic properties

and design guidelinesIAD-A124016] p470 N83-25795

BBlhrle Applied Research, Inc, Jericho, N Y


Boeing Commercial Airplane Co, Seattle, WashApplications of advanced upper surface blowing


Progress in propulsion system/airlrame structuralintegration[AIAA PAPER 83-1123] p 437 A83-36234


California Unlv, Los AngelesCoupled flap-lag-torsional dynamics of hmgeless rotor

blades in forward flight p 433 A83-33506

C-1

California Univ., Riverside.


California Univ, RiversideHigh altitude jet fuel photochemistry

(AD-A125035I p 471 N83-27035Calspan Corp, Buffalo, N Y

Lateral flying qualities of highly augmented fighteraircraft, volume 1(AD-A118070J p443 N83-26835

Canyon Research Group, Inc, Westlake Village, CalifSimulator design features for carrier landing Part 2

In-simulator transfer of training(AD-A124024] p466 N83 25733

Cincinnati Univ, OhioThe effect of microstructure on the fatigue behavior of

Ni base superalloys p 469 A83-36166Committee on Commerce, Science, and Transportation

(U S Senate)NASA authorization for fiscal year 1984

[GPO-19-200] p487 N83-27921Comptroller General of the United States, Washington,

DCA strategy is needed to deal with peaking problems at

international airports[GAO/GGD-83-4J p 429 N83-25683


Computational Mechanics Consultants, Knoxvllle,Tenn

An assessment of factors affecting prediction ofnear field development of a subsonic VSTOL |et incross-flow(AD-A124583] p 441 N83 25699

Dayton Univ, OhioNumerical simulation of airfoil ice accretion

[AIAA PAPER 83-0112] p 428 A83-36042High frequency fatigue of turbine blade material

[AD-A124585] p 458 N83 25713Defence and Civil Inst of Environmental Medicine,

Downsview (Ontario)Theory underlying the peripheral vision horizon device

(AD-A124426] p 445 N83-25710Defense Mapping Agency Aerospace Center, St Louis,

MoPrecision navigational filmstnps for use in DOD aircraft

[AD-A124761] p 432 N83-25688Department of Energy, Bartlesville, Okla

Thermodynamics of organic compounds[AO-A125022] p 483 N83-27895

Detroit Diesel Allison, Indianapolis, IndApplication of 3D aerodynamic/combustion model to

combustor primary z.one study[AIAA PAPER 83-1265] p 454 A83-36316

Deutsche Forschungs- und Versuchsanstalt fuer Luft-und Raumfahrt, Goettlngen (West Germany)


Ecole Nationale Supeneure des Telecommunications,Paris (France)

Numerical treatment of Doppler radar signals[ENST-E-82014] p 478 N83-27114

ECON, Inc, Princeton, N JStatus trends and implications of carbon fiber material

use[PB83-147751] p 471 N83-26934

Edgerton, Germeshausen and Grler, Inc, Salem, MassPhase 2A bench model development tactical rubidium


European Space Agency, Pans (France)Evaluation of aerodynamic derivatives from Do-28-TNT

free-flight model tests[ESA-TT-784] p 442 N83-25706

Federal Aviation Administration, Washington, D CFAA aviation forecasts Fiscal years 1983-1994

[AD-A124611] p416 N83-25652General aviation activity and avionics survey

[AD-A124595] p416 N83-25653Aviation Executive Conference

[AD-A124581] p 416 N83-25654Runway surface condition sensor specification guide

[AC-150/5220-13A] p 465 N83-25728

A survey of helicopter and ambient urban noise levelsin Phoenix, ArizonaIAD-A123856] p 479 N83-26322

Federal Aviation Agency, Atlantic City, N JDigital flight control system validation

[AD-A124506] p 462 N83-26847Flying Training Wing (323d), Mather AFB, Calif

AICUZ (Air Installation Compatible Use Zone) report(AD-A124974] p 483 N83-27801

Garrett Turbine Engine Co, Phoenix, ArizExperiments in dilution jet mixing

[AIAA PAPER 83-1201] p 475 A83-36277Three-dimensional compressible viscous analysis of

mixer nozzlesIAIAA PAPER 83-1401] p 422 A83-36391

General Accounting Office, Washington, D CGreater benefits to be gained from DoD flight

simulators[AD-A123713] p 466 N83-25731

General Dynamics Corp, Fort Worth, TexForce and pressure measurements on a research model

with a low-, mid- and T tail at Mach numbers of 0 60 to0 90 Volume 2 Tabulated data[AD-A124068] p 425 N83-25676

General Electric Co, Cincinnati, OhioThe aerodynamic design and performance of the

General Electric/NASA EEE fanIAIAA PAPER 83-1160] p 451 A83 36252

General Motors Corp , Indianapolis, IndAdvanced propfan engine characteristics and

technology needs[AIAA PAPER 83-1155] p 450 A83-36250

George Washington Univ, Hampton, VaMethod for calculating effects of a propfan on aircraft

aerodynamics at subsonic speeds[AIAA PAPER 83-1216] p 420 A83 36287


Georgia Inst of Tech, AtlantaHelicopter rotor loads using discretized matched

asymptotic expansions[NASA-CR-166092] p 423 N83 25658


Goodyear Aerospace Corp , Akron, Ohio1983 LTA technology assessment

[AIAA PAPER 83-1617] p 437 A83-36406

HHouston Univ, Tex

The remote link unit A demonstration of operationalperformance Part 3 Design manual, volume 1[ADA124621] p 476 N83-25934




Hughes Helicopters, Culver City, CalifUltrasonic weld bonding of helicopter primary


INFOCOM, Crawley (England)Foreign Technology Alert - Bibliography Transportation

safety[PB83-101659] p430 N83-25686

Institut de Mecanique des Fluides de Lille (France)Materials and modelling technology for cryogenic

environment p 465 N83-25723

Jet Propulsion Lab, California Inst of Tech,Pasadena

Entrainment and mixing in thrust augmenting electors[AIAA PAPER 83-0172] p419 A83-36046

CORPORA TE SOURCE

KKaman Avidyne, Burlington, Mass

NOVA-2S correlation with KC-135A fuselage shock tubetest results[AD-A124013) p466 N83-25732

Kansas Univ Center for Research, Inc, LawrenceAnalysis of nonplanar wing-tip-mounted lifting surfaces


Lightning Technologies, Inc, Pittsfield, MassAircraft lightning-induced voltage test technique

developments[NASA-CR-170403] p 442 N83 26829

Lockheed Corp, Burbank, CalifAdvanced manufacturing development of a composite

empennage component for L-1011 aircraft[NASA-CR-17265B] p 440 N83-25692

Advanced manufacturing development of a compositeempennage component for L-1011 aircraft[NASA-CR-172659] p 440 N83 25693


Lockheed-Georgia Co, MariettaAerodynamic design of propfan powered transports

[AIAA PAPER 83-1213] p 437 A83 36285Experimental studies of the separating confluent


MMcDonnell-Douglas Corp, St Louis, Mo


McDonnell-Douglas Research Labs, St Louis, MoHigher-order computational methods for transonic

wing/body flowfields[AD-A124079] p 426 N83-25679

Mitre Corp, McLean, VaFAA integrated noise model validation Analysis of air


NNational Aeronautics and Space Administration,

Washington, D C1983 LTA technology assessment

[AIAA PAPER 83-1617] p 437 A83-36406National Aeronautics and Space Administration Ames

Research Center, Moffett Field, CalifApplications of advanced upper surface blowing




p 474 A83-36085Spectral decontamination of a real-time helicopter


The man-vehicle systems research facility A new NASAaeronautical R & D facility[AIAA PAPER 83-1098] p 463 A83-36218


Pressures measured in flight on the aft fuselage andexternal nozzle of a twin-let fighter[NASA-TP-2017] p 424 N83-25665

A flight-test and simulation evaluation of the longitudinalfinal approach and landing performance of an automaticsystem for a light wing loading STOL aircraft[NASA-TM-84270] p 461 N83 26845




C-2

CORPORA TE SOURCE Toledo Univ, Ohio.

National Aeronautics and Space Administration FlightResearch Center, Edwards, Calif

In-flight acoustic test results for the SR-2 and SR-3advanced-design propellers(AIAA PAPER 83-1214] p 452 A83-36286

National Aeronautics and Space AdministrationGoddard Space Flight Center, Greenbelt, Md

RF radiation from lightning correlated with aircraftmeasurements during storm hazards-82(NASA-TM-85007] p 479 N83-27537

National Aeronautics and Space AdministrationLangley Research Center, Hampton, Va

Recenl studies at NASA-Langley of vortical flowsinteracting with neighboring surfaces

p417 A83-33972Flight management concepts development for fuel

conservation p 447 A83-35843Evaluation of a surface panel method coupled with


Empennage/afterbody integration for single andtwin-engine fighter aircraft[AIAA PAPER 83 1126] p 420 A83-36235



Space-station crew safety requirementsp 467 A83-36408

Natural laminar flow data from lull-scale flight andwind-tunnel experiments p 422 A83-36409


Effect of empennage location on twin-engineafterbody-nozzle aerodynamic characteristics at MachNumbers from 0 6 to 1 2[NASA-TP-2116] p424 N83-25666



Some historical trends in the research and developmentof aircraft[NASA-TM-84665] p417 N83-26785


Effects of varying podded nacelle nozzle installationson transonic aeropropulsive characteristics of a supersonicfighter aircraft[NASA-TP2120] P427 N83-26821


National Aeronautics and Space Administration LewisResearch Center, Cleveland, Ohio

Acoustic modal analysis of a full-scale annularcombustor[AIAA PAPER 83-0760] p 481 A83-33486



Design analysis of a self-acting spiral-groove ring sealfor counter-rotating shafts[AIAA PAPER 83-1134] p 474 A83-36239

The aerodynamic design and performance of theGeneral Electric/NASA EEE fan[AIAA PAPER 83-1160] p 451 A83-36252

Experiments in dilution jet mixing[AIAA PAPER 83-1201] p 475 A83-36277



NASA low-speed centrifugal compressor forfundamental research[AIAA PAPER 83-1351) p 464 A83-36353


Experimental results of a deflected thrust V/STOLnozzle research program[NASATM-83069] p 423 N83-25657



Design analysis of a self-acting spiral-groove ring sealfor counter-rotating shafts[NASA-TP 2142] p 458 N83-25712


A compact inflow control device for simulating flight tannoise[NASA-TM-83349] p 482 N83-26643

Dynamic distortion in a short s-shaped subsonic diffuserwith flow separation[NASA-TM-84312] p 459 N83-26838


JT150 1/2-scale nozzle |et noise experiment andcomparison with prediction[NASA-TM-83370] p 482 N83-27793

Low flight speed acoustic results for a supersonic inletwith auxiliary inlet doors[NASATM-83411] p 482 N83-27794

National Aeronautics and Space AdministrationMarshall Space Flight Center, Huntsville, Ala


Damping seal for turbomachmery[NASA CASE-MFS-25842-1 ] p 477 N83-26080

National Severe Storms Lab, Norman, OklaScanning strategies tor next generation weather radars

A study based on lifetimes of convective atmosphericphenomena hazardous to aviation(FAA-RD-82-69) p 476 N83-25929

National Transportation Safety Board, Washington, DC

Aircraft accident report IBEX Corporation Gates Learjet23, N100TA, Atlanta, near Savannah Georgia, 6 May1982[PB83-910401] p430 N83-26827

Naval Air Development Center, Warmmster, PaA preliminary assessment of helicopter/VSTOL handling


Statistical review of counting accelerometer data forNavy and Marine fleet aircraft[AD-A124966] p 443 N83-26834

Naval Postgraduate School, Monterey, CalifSH-3 helicopter/Global Positioning System integration

analysis[AD-A125005] p 432 N83-25691

Automatic control and data acquisition system forcombustion laboratory applications[AD-A125195J p 470 N83-25829

Finite element program for calculating flows inturbomachmes with results for NASA task-1 compressor[AD-A124987) p 460 N83-26841



Naval Ship Research and Development Center,Bethesda, Md


Office National d'Etudes et de RecherchesAerospatiates, Toulouse (France)


Ohio State Unlv, ColumbusTransient heat flow along urn-directional fibers in


Oklahoma State Unlv, StillwaterThe performance of an annular vane swirler

[AIAA PAPER 83-1326] p 455 A83-36340Oxford Univ (England)


Pennsylvania State Univ, University ParkEnd wall flow characteristics and overall performance

of an axial flow compressor stage[NASA CR-3671 ] p 427 N83-26819

Investigation of the coupling of unsteady lift to low orderacoustic duct modes in an axial flow fan(AD-A124819] p 483 N83-27796

Pratt and Whitney Aircraft Group, East Hartford, ConnEjector nozzle test results at simulated flight conditions

for an advanced supersonic transport propulsion system| AIAA PAPER 83 1287] p 454 A83-36323


Princeton Univ , N JDesign of dry-friction dampers for turbine blades

p 450 A83-35883Purdue Univ, Lafayette, Ind

Effect of humidity on jet engine axial-flow compressorperformance p 448 A83-35856

RAND Corp, Santa Monica, CalifDevelopment and production cost estimating

relationships for aircraft turbine engines[AD-A123753J p 459 N83-25714

Research Inst of National Defence, Linkoepmg(Sweden)

Simulation program of rotary wings[FOA-C-30308-E1] p 443 N83-26836

Laser safety of air bathymetry[FOA-C-30292-E1] p 478 N83-27210

Rocketdyne, Canoga Park, CalifHybrid hydrostatic/ball bearings in high-speed

turbomachmery[NASACR-168124] p 478 N83-27213

Rolls-Royce Ltd , Derby (England)Method of studying the operating temperature of gas

turbines[PNR-90159] p 460 N83 26842

Royal Aircraft Establishment, Bedford (England)Early experience in using the Cryogenic Test Facility

at RAE Bedford, England p 465 N83-25726Royal Aircraft Establishment, Farnborough (England)


Royal Inst of Tech , Stockholm (Sweden)Experimental study of strength and existence domain

of ground-to-air inlet vortices by ground board staticpressure measurements[PB83-144865] p 460 N83-26843

Sandia Labs, Albuquerque, N MexSandia Helicopter Acoustic Detector (SHAD)

[DE82-018925] p 483 N83-27803Santa Clara Univ, Calif

Derivation of the fundamental equation of soundgenerated by moving aerodynamic surfaces

p 482 A83-36096Slnacon (John B) Associates, Holllster, Calif


Southwest Research Inst, San Antonio, TexEmergency fuels technology

[AD-A125275] p 471 N83-25904Spectron Development Labs, Inc, Costa Mesa, Calif


Systems Technology, Inc, Hawthorne, CalifProposed MIL standard and handbook Flying qualities

of air vehicles Volume 2 Proposed MIL handbook[AD-A123726] p 441 NB3-25704

Techmon - Israel Inst of Tech , HaifaNumerical calculation of nonlinear aerodynamics of

wing-body configurations p 420 A83-36076Techmsche Hogeschool, Delft (Netherlands)


Textron Bell Helicopter, Fort Worth, TexCorrelation and evaluation of mplane stability

characteristics for an advanced bearmgless mam rotor[ N AS A-CR-166448] p 440 N83-25695

Toledo Univ, OhioNumerical simulation of electrothermal de-icing


C-3

Transportation Research and Marketing, Salt Lake City, Utah.

Transportation Research and Marketing, Salt LakeCity, Utah

Transportation Energy Conservation Through Land UsePlanning[PB83-148387J p 475 N83-25919

Tuskegee Inst, AlaA comprehensive method for preliminary design

optimization of axial gas turbine stages tl Codeverification| AIAA PAPER 83-1403 ] p 456 A83-36393

UUnited Technologies Corp , East Hartford, Conn

Importance of inlet boundary conditions for numericalsimulation of combustor flows| AIAA PAPER 83-1263] p 454 A83-36314

United Technologies Corp , Stratford, ConnExperimental study of main rotor/tail rotor/airframe

interactions in hover Volume 1 Text and figuresINASA-CR-166485] p 427 N83-26820

Vigyan Research Associates, Inc, Hampton, VaMethod for calculating effects of a propfan on aircraft

aerodynamics at subsonic speeds| AIAA PAPER 83-1216] p 420 A83-36287

Virginia Polytechnic Inst and State Unlv, BlacksburgInjection, atomization, ignition and combustion of liquid

fuels in high-speed air streams(AD-A125237] p 471 N83-27033

C-4

CONTRACT NUMBER INDEX


Typical Contract NumberIndex Listing

NAS3-22133

AF PROJ 1900AF PROJ 2003

AF PROJ 2277AF PROJ 2307AF PROJ 2308

AF PROJ 2402AF PROJ 2403AF PROJ 2418AF PROJ 8809AF-AFOSR-ISSA-81 -00029AF- AFOSPUSSA-82-00012AF-AFOSR-2954E-76AF-AFOSR-3485-78AF-AFOSR-3640-78AF-AFOSR-80-0065DA PHOJ 1L7-72733-AH-20DAAG29-82-K-0029

DAAK51-79-C-0045DAAK70-80-C-0001DAAK70-82-C-0001DARPA ORDER 3430DE-AC04 76DP-00789DOT-FA01-81-C-10041DOT-FA79WA-4310DTFA01-80-Y-10524OTFA01-82-C-10003EPA-68-03-2857F04701-78-C-0144F08635-80-C-0359F1628-81-C-0055F29601-81-C-0031F33615-7S-C-2091F33615-78-C-2401F33615-78-C-3608F33615-79-C-3009F33615-7S-C-3618F33615-79-C-5108F33615-79-C-5119F33615-80-C-1095

F33615-80-C-3001F33B15-80-C-3604F33657-72-C-0242F33657-77-C-0391

p 42 N83- 10044

NASA; ACCESSION

| NUMBER

uphanuffiencaiiyxintract number,documents that

if research doneid in ascendingnbers appeanng>s the number byin the abstractnumber is the

may be found

p 471 N83-27035p 476 N83-25934p476 N83-25935p 476 N83-25938P476 N83-25939p 477 N83-25990p 471 N83-26929p 471 N83-27033p 483 N83-27895p 443 N83-26832p 441 N83-25704p458 N83-25713p 466 N83-25732p 419 A83-36046p 483 N83-27895p 466 N83-26792p 471 N83-27033p 471 N83-26929p469 A83-36166p 471 N83-25904p468 A83-35247p 448 A83-35854p477 N83-26081p 471 N83-25904p 471 N83-25904p 455 A83-36346p 483 N83-27803p431 A83-35192p469 A83-36240P476 N83-25929p 479 N83-26320p 471 N83-26934p420 A83-36078p 471 N83-27035p477 N83-25990p 466 N83-25732p 451 A83-36254p448 A83-35856p436 A83-36214p 421 A83-36292p443 N83-26835p458 N83-25713P472 A83-33650p476 N83-25934p 476 N83-25935p476 N83-25938p 476 N83-25939P420 A83-36291p 441 N83-25704p457 A83-36412P455 A83-36346

F49620-79-0189F49620-82-C-0018F49620-82-K-OOOaMIPR-79-102MIPR-79-404NAG3-204NAG3-221NAG3-62NAGS 65NAS1-1 4000

NAS1-14741NAS1-16028NAS1-16150

NAS1 -16742NAS1-16817

NAS2-10770NAS2-10934NAS2-11120NAS2-11161NAS2-11269NA.S2-19573NAS3-22480NAS3-22738NAS3-22762NAS3-23046NAS3-23524NAS3-74NAS4-2930NCC2-191NSERC-A-1613NSERC-A-3378NSG-1578

NSG 1633NSG 3032NSG-3263NSG-3295N00014-80-C-0481N00014-82-C-0340N00019-79-C-0634N00019-80-C-0225N00024-79-C-6043NQG14Q-80-C-O097N00167-81-C-0057N61339-81-C-0105N62269-80-MP-00034N62269-81-C-0395N62269-82-C-0233RF41411801WF4 1400000

505-15-83505-31-32505-31-51505-31-53-10505-32-42505-33-32505-33-43-09505-34-01505-34-03-06505-40-02505 40-5B505-42-1 1

505-43-02505-43-22505-43-23-01505-43-43-01505-43-43-04506-51-1151254-14532-02-11

p482p459p475p425p425p448p450p 448p428p440p440p440P442p427p447p421p420p423p423p427p467p437p426p440p483p478p426p454p450p454p455p442p482p484p484p433p435p424p427p469p456p422p425p470p457p483p470p426p466p419p441p441p425p441p 461p427p424p483p424p458p470p426p462p461p459p458p440p427p«23p459p 424p417p427p478p442p461

A83-36077N83-25714AB3-36354N83-25675N83-25675A83-35856A83-35883A83-35856A83-36042N83-25692N83-25693N83-25694N83-26831N83-26822A83-35842A83-36363A83-36287N83-25658N83-25659N83-26820N83-26849A83-36285N83-26818N83-25695N83-27645N83-27213N83-26816A83-36316A83-36250A83-36314A83-36340N83-26829A83-36096A83-34852A83-348520,83-33506A83-35948N83-25667N83-26819A83-36166A83-36393A83-36403N83-25676N83-25795A83-36412N83-27796AB3-36243N83-25679N83-25733A83-36046N83-25699N83-25700N83-25676N83-25700N83-25716N83-26819NB3-25662N63-2784SN83-25660N83-25712N83-25790N83-26815N83-26846N83-26844N83-26838N83-25711N83-25695N83-26820N83-2S657N83-26839N83-25666N83-26785N83-26821N83-27149N83-26829N83-26845

D-1

REPORT NUMBER INDEX


Typical Report NumberIndex Listing

NASAACCESSION

NUMBER

MICROFICHESYMBOL

EWA-82 R-21 p69 N83-1166r

PAGENUMBER

NASADOCUMENT

SYMBOL

Listings in this index are arranged alphanumencallyby report number The page number indicates thepage on which the citation is located Theaccession number denotes the number by whichthe citation is identified An astensk (*) indicatesthat the item is a NASA report A pound sign (#)indicates that the item is available on microfiche

A-8993A-9143A-9297A-9332

AC-150/5220-13A

AD-A118070AD-A122248AD-A122667AD-A122926AD-A123188AD-A123281AD-A123713AD-A123726AD-A123753AD-A123782AD-A123848AD-A123656AD-A123932AD-A123961AO-A123981AD-A123982AD-A 124013AD-A124016AD-A 124024AD-A124068AD-A124079AD-A124097AD-A124426AD-A 124462AD-A124468AD-A124506AD-A124523AD-A124566AD-A124581AD-A124583AD-A124585AD-A124595AD-A124611AD-A 124619AD-A124620AD-A124621AD-A124622AD-A124645AD-A124661AD-A 124662AD-A124663AD-A124667AD-A124670AD-A124680AD-A124681AD-A124695AD-A124699AD-A124700

p 461 N83-26845- #p 478 N83-27148' #p 462 N83-26846' #p 478 N83-27149' ft

p465 N83-25728 ft

p443P427p417p471P429p 440P466p 441P459p 466p417P479P459P487P416p426p466p470P466P425P426P479P445p477p 441P462P425p441p416p441p458p416p416p476p476p476p476p477p481p477p424p461p440p479p 444p425p440p481

N83-26835 ftN83 26824 ftN83-26787 ftN83-26929 ftN83 25684 ftN83-25696 ftN83-25731 ftN83-25704 ftN83-25714 ftNOT 25730 ftN83-25656 ftN83-26322 #N8325715 ftN83-26783 itN83-25655 ftN83-25677 ftN83-25732 ftN83 25795 ftN83-25733 ftN83-25676 ftN83-25679 ftN83-26320 ftN83-25710 ftN83-25990 ftN83-25700 ftN83-26847 #N83-25675 #N83-25703 ftN83-25654 ftN83-25699 ftN83-25713 #N83-25653 ftN83-25652 ftN83-25939 ftN83-25938 ftN83-25934 ftN83-25935 ftN83-26081 ftN83-26637 #N83-26099 ftN83-25669 ftN83-25716 ftN83-25698 #N83-26345 ftN83-25709 #N83-25670 ftN83-25697 ftN83-26501 ft

AD-A124703AD-A124713AD-A124715AD-A124716AD-A124720AD-A124722AD-A124732AO-A124739AD-A124741AD-A124749AD-A124757AD-A124761AD-A124770AD-A124771AD-A124791AD-A124792AD-A124819AD-A124837AD-A124B52AD-A124870AD-A124871AD-A124882AD-A124896AD-A124949AD-A 124966AD-A124974AD-A124987AD-A 125005AD-A125022AD-A 125025AD-A125035AD-A125036AD-A125195AD-A125237AD-A125266AD A125270AD-A125275AD-A125883

AFAPL-TR-79-2126

AFESC/ESL-TR-82-38

AFGL-TR-82-0366

AFIT-CI NR-82-63D

AFIT-LSSR-23-82AFIT-LSSR-56-82AFIT-LSSR-70-82

AFIT/DS/AA/82-1

AFIT/GAE/AA/79D-4AFIT/GAE/AA/81D-19AFIT/GAE/AA/82D-13AFIT/GAE/AA/82D-15AFIT/GAE/AA/82D-16-PT 1AFIT/GAE/AA/82D-19AFIT/GAE/AA/82O-1AFIT/GAE/AA/82D-23AFIT/GAEÂA/820-27AFIT/GAE/AA/82D-28AFIT/GAE/AA/82D-30AFIT/GAE/AA/82D-34AFIT/GAE/AA/82D-3AFIT/GAE/AA/82D-4AFIT/GAE/AA/82D-8AFIT/GAE/AA/82D-9

AFIT/GAE/EE/82D-1

AFIT/GAE/82D-10

AFIT/GCS/EE/82D-12

AFIT/GCS/MA/82D-4

AFIT/GE/EE/82D-24AFIT/GE/EE/82D-43AFIT/GE/EE/82D-45AFIT/GE/EE/82D-55AFIT/GE/EE/82D-56

p424 N83-25668 #p 430 N83-25685 #p 461 N83-25719 #p461 N83-25718 ftp 425 N83-25674 #p425 N83-25673 #p 441 N83-25701 #p470 N83-25793 #p461 N83-25717 #P476 N83-25948 #p 441 N83-25702 #P432 N83-25688 #p 442 N83-26830 #P425 N83-25671 #p 477 N83-26103 #P477 N83-26023 #p483 N83-27796 #p 459 N83-26840 #p 466 N83-25735 #p443 N83-26833 ftp 462 N83-26848 #p 432 N83-26828 #p428 N83-26825 ftp 443 N83-26832 #P443 N83 26834 #p 483 N83-27801 ftP460 N83-26841 #p 432 N83-25691 ftP483 N83-27895 #p471 N83-27034 #P471 N83-27035 #p 481 N83-27624 ftP470 N83-25829 #p 471 N83-27033 ftP478 N83-27260 #p442 N83-25705 #p 471 N83-25904 ftp479 N83 26367 #

P417 N83-26787 #

p 471 N83-27035 #

P479 N83-26367 #

p478 N83-27260 #

p 466 , N83-25730 #p417 N83-25656 #p416 N83-25655 #

p 428 N83-26825 ft

p 425 N83-25674 #p459 N83-26840 #p 441 N83-25701 #p470 N83-25793 #p 477 N83-26099 #P461 N83-25717 #P441 N83-25702 #P424 N83 25668 #P461 N83-25719 #p 425 N83-25671 #p425 N83-25673 #p424 N83-25669 #p477 N83-26023 #P442 N83-26830 #p 477 N83-26103 #p461 N83-25718 #

P462 N83-26848 #

P425 N83-25670 #

p 466 N83-25735 #

p481 N83-26637 #

P444 N83-25709 #p 440 N83-25697 #p430 N83-25685 #P432 N83-26828 #P476 N83-25948 #

AFIT/GE/EE/82D 61AFIT/GE/EE/82D-72

AFIT/GOR/MA/82D-2

AFLRL-155

AFOSR-83-0025TRAFOSR-83-0047TR

AFWAL-TR 81-1 131-PT-1AFWAL-TR-81-1 131-PT-2AFWAL-TR 81 1131-PT-3 VOL-1AFWAL-TR 81 -11 31 -PT -3 VOL-2AFWAL-TR-81-3171-VOL 1AFWAL-TR 81 4134AFWAL-TR-82-3043AFWAL-TR-82-3061AFWAL-TR 82-3081 -VOL-2AFWAL-TR-82-4151AFWAL-TR-82 4201

AFWL-TR 82-101

AGARD-AR-189

AGARD-BUL-83/1

AIA PAPER 83-1046

AIAA PAPER 83-001 1AIAA PAPER 83-0112AIAA PAPER 83-01 14AIAA PAPER 83-0172AIAA PAPER 83-0760AIAA PAPER 83-0762AIAA PAPER 83-1045AIAA PAPER 83-1047AIAA PAPER 83-1048AIAA PAPER 83-1049AIAA PAPER 83-1 051AIAA PAPER 83-1052AIAA PAPER 83-1053AIAA PAPER 83-1054AIAA PAPER 83-1055AIAA PAPER 83-1057AIAA PAPER 83-1058AIAA PAPER 83-1059AIAA PAPER 83-1061AIAA PAPER 83-1062AIAA PAPER 83-1063AIAA PAPER 83-1064AIAA PAPER 83-1075AIAA PAPER 83-1076AIAA PAPER 83-1078AIAA PAPER 83-1079AIAA PAPER 83-1080AIAA PAPER 83-1086AIAA PAPER 83 1087AIAA PAPER 83-1088AIAA PAPER 83-1090AIAA PAPER 83-1091AIAA PAPER 83-1092AIAA PAPER 83-1097AIAA PAPER 83-1098AIAA PAPER 83-1099AIAA PAPER 83-1101AIAA PAPER 83- 11 23AIAA PAPER 83-1 126AIAA PAPER 83-1127AIAA PAPER 83-1 130AIAA PAPER 83-1132AIAA PAPER 83-1 133AIAA PAPER 83-1 134AIAA PAPER 83-1137AIAA PAPER 83-1138AIAA PAPER 83 1143AIAA PAPER 83-1 147AIAA PAPER 83-1155AIAA PAPER 83 11 59AIAA PAPER 83-1160AIAA PAPER 83 1161AIAA PAPER 83-1 163

p479 N83-26345 #p 481 N83-26501 ft

p443 N83-26833 #

p471 N83-25904 #

p471 N83-27033 #p 483 N83-27895 #

p 476 N83-25939 #p476 N83-25938 ftp 476 N83 25934 ftp476 N83-25935 ftp 443 N83-26835 #p 487 N83-26783 #P443 N83-26832 ftp 471 N83 26929 #p441 N83-25704 ftp 458 N83-25713 ftp487 N83-26783 #

P466 N83-25732 #

p426 N83-25682 #

p417 N83-26786 #

p415 A83-36459 #

p474 A83 36039' #p 428 A83-36042' ftp428 A83 36043' #P419 A83-36046' #p481 A83-33486' #p 481 A83 33487' #p415 A83-36458 #P416 A83 36471 #p 437 A83-36460 #P439 A83-36472 ftp 438 A83-36461 ftp438 A83-36462 #p 457 A83 36463 #p438 A83-36465 #p 438 A83-36466 #p438 A83 36468 #p438 A83-36469 ftp 439 A83-36474 #P432 A83 36470 #p 439 A83-36473 ftp438 A83-36467 #p 457 A83-36464 #p436 A83-36204 ftp 436 A83-36205 #p436 A83-36206 #p 443 A83 36207 #p 464 A83-362221 ftp480 A83-36210 ftp436 A83-36211' ftP480 A83-36212 #p436 A83-36214 #p437 A83-36215 ftp463 A83-36216 #p463 A83-36217 ftp463 A83-36218'#p463 A83-36219 ftP474 A83-36221 #p437 A83-36234' #p420 A83-36235' ftp 450 A83-36236 ftp 475 A83-36405 #P474 A83-36237 #p450 A83-36238 #p 474 A83-36239' #p 469 A83-36240 #p 469 A83-36241 #p 470 A83-36243 #p 450 A83-36244 #P450 A83-36250'#p 451 A83-36251 #p451 A83-36252' #p 451 A83-36253 #p 451 A83-36254 #

E-1

AIAA PAPER 83-1169 REPORT NUMBER INDEX

AIAA PAPER 83-1169AIAA PAPER 83-1171AIAA PAPER 83-1173AIAA PAPER 83-1174AIAA PAPER 83-1176AIAA PAPER 83-1201AIAA PAPER 83-1209AIAA PAPER 83-1212AIAA PAPER 83-1213AIAA PAPER 83-1214AIAA PAPER 83-1216AIAA PAPER 83-1224AIAA PAPER 83-1225AIAA PAPER 83-1229AIAA PAPER 83-1230AIAA PAPER 83-1232AIAA PAPER 83-1233AIAA PAPER 83-1234AIAA PAPER 83-1235AIAA-PAPER 83-1236AIAA PAPER 83-1237AIAA PAPER 83-1238AIAA PAPER 83-1239AIAA PAPER 83-1240AIAA PAPER 83-1241AIAA PAPER 83-1263AIAA PAPER 83-1265AIAA PAPER 83-1285AIAA PAPER 83-1287AIAA PAPER 83-1288AIAA PAPER 83-1290AIAA PAPER 83-1291AIAA PAPER 83-1292AIAA PAPER 83-1293AIAA PAPER 83-1294AIAA PAPER 83-1297AIAA PAPER 83-1300AIAA PAPER 83-1324AIAA PAPER 83-1326AIAA PAPER 83-1338AIAA PAPER 83-1339AIAA PAPER 83-1342AIAA PAPER 83-1351AIAA PAPER 83-1352AIAA PAPER 83-1354AIAA PAPER 83-1356AIAA PAPER 83-1358AIAA PAPER 83-1359AIAA PAPER 83-1367AIAA PAPER 83-1368AIAA PAPER 83-1369AIAA PAPER 83-1374AIAA PAPER 83-1377AIAA PAPER 83-1401AIAA PAPER 83-1403AIAA PAPER 83-1405AIAA PAPER 83-1406AIAA PAPER 83-1407AIAA PAPER 83-1408AIAA PAPER 83-1409AIAA PAPER 83-1410AIAA PAPER 83-1411AIAA PAPER 83-1579AIAA PAPER 83-1588AIAA PAPER 83-1591AIAA PAPER 83-1597AIAA PAPER 83-1617AIAA PAPER 83-2017

AIAA 83-1082AIAA 83-1083AIAA 83-1094

AIAA-83-0680

AR-002-900-PT-10

ARL-AERO-TECH-MEMO-341-PT

ARL/PSU-TM-82-137

ARL/STRUC-TM-345

B-206887B-208444

CALSPAN-6645-F-8-VOL-1

CRG-TR-82-011

DCIEM-TC-82-C-57

DE82-018925

DFVLR-FB-82-17

p423p420p420p451p451p475p452p452p437p452p420p420p421p452p452p452p453p453p453p453p453p453p453p444p454p454p454p454p454p421P423p444p 444p444p455p455p457p455p455p455p458p455p464p475p421p422p464p455p421p421p421p456p456p422p456p456p456p456p457p457p467p457p429p429p429p429p437p422

p480p464p437

p482

p427

'-1 Op 427

p483

p 441

p432p429

p443

p466

p445

p483

p442

A83-36922 #A83-36258 #A83-36259 #A83-36260 ttA83-36261 ttA83-36277' #A83-36282 ttA83-36284 ttA83-36285' #A83-36286' ttA83-36287' ttA83-36291 ' #A83-36292 ftA83-36293 ttA83-36294 #A83-36295 ttA83-36296 #A83-36297 ttA83-36298 ttA83-36299 ttA83-36300 ttA83-36301 #A83-36302 ttA83-36303 ttA83-36304 ttA83-36314' #A83-36316' #A83-36322 #A83-36323' #A83-36324' #A83-36924 #A83-36325 ttA83-36326 #A83-36327 ttA83-36328 ttA83-36329 ttA83-36412 #A83-36339 ttA83-36340' ttA83-36346 ttA83-36925 ttA83-36347 ttA83-36353' ttA83-36354 ttA83-36355 #A83-36414 ttA83-36356 ttA83-36357 #A83-36363' ttA83-36364 ttA83-36365 #A83-36367 #A83-36368 ttA83-36391 ' ttA83-36393' ttA83-36394 ttA83-36395 ttA83-36396 ttA83-36397 ttA83-36398 ttA83-36399 ttA83-36400 #A83-36953 ttA83-36954 ttA83-36951 ttA83-36952 ttA83-36406' ttA83-36403 tt

A83-36223 #A83-36224 #A83-36225 tt

N83-26643' tt

N83-26824 tt

N83-26824 tt

N83-27796 tt

N83-25703 tt

N83-25687 ttN83-25683 tt

N83-26835 tt

N83-25733 #

N83-25710 tt

N83-27803 tt

N83-25706 tt

DOT-1 -82-50

DRIC-BR-86199

DRL-003DRL-003DRL-003

DTNSRDC/ASED-CR-03-82

DTNSRDC/ASED-82/09

E-1253E-1451E-1539E-1558E-1606E-1618E-1636E-1675E-1694E-1695

ENST-E-82014

EPA-600/2-82-103

ERP-810

ESA-TT-784

FAA-APO-81-9FAA-APO-83-1

FAA-CT-82-54

FAA-EE-82-19FAA-EE-82-20

FAA-MS-82-5

FAA-RD-82-69

FOA-C-30292-E1FOA-C-30308-E1

FTD-ID(RS)T-1561-82

FZA-540-VOL-2

GAO/AFMD-83-34

GAO/FPCD-83-4

GAO/GGD-83-4

GPO-19-200

H-1161

HHI-82-261

INFO- FT/82-03"

ISBN-92-835-1 445-9

KA-TR-202

KTH-AERO-TN-62

KU-FRL-427-1

L-15525L-15527

LG-82-ER-0184

LR-28743LR-28843LR-29058LR-355

LT-82-132

MDC-O0773

MTR-82W162

N ADC- 13920-2NADC-8 1023-60NADC-81 177-60NADC-8 1293-60

NAS 1 1582528MAS 1 1583069NAS 1 1583343

p475

p426

p440p440p 440

p426

p425

p458p459p423p458p482p470p482p424p482p459

p478

p471

p479

p442

p416p416

p462

p479p479

p416

p476

p478p443

p459

p425

p432

p466

p429

p487

p424

p477

p430

p426

p466

p460

p424

p427p424

p427

p440p440p 440p479

p442

p426

p479

p443p461p 441p441

p470p423p458

N83-25919

N83-25677

N83-25692*N83-25693'N83-25694'

N83-25679

N83-25675

N83-25712'N83-26839'N83-25657'N83-25711-N83-26643'N83-25790'N83-27793'N83-25662'N83-27794'N83-26838'

N83-27114

N83-26934

N83-26367

N83-25706

N83-25654N83-25652

N83-26847

N83-26320N83-26322

N83-25653

N83-25929

N83-27210N83-26836

N83-25715

N83-25676

N83-25687

N83-25731

N83-25683

N83-27921

N83-25665'

N83-26081

N83-25686

N83-25682

N83-25732

N83-26843

N83-25667'

N83-26821 'N83-25666'

N83-26822'

N83-25692'N83-25693'N83-25694'N83-27476

N83-26829'

N83-25679

N83-26320

N83-26834N83-25716N83-25699N83-25700

N83-25854'N83-256571

N83-25711'

tt

tt

tttttt

tt

#

#tt#tttt#tttttt#

#

#

#

#

##

#

tttt

#

tt

##

#

tt

#

#

#

#

#

tt

tt

tt

tt

#

#

##

tt

tt#tt#

#

#

#

#tttt#

tt##

NAS 1 1583349NAS 1 1583357NAS 1 1583370NAS1 1583398NAS 1 1583411NAS 1 1584270NAS 1 1584305NAS 1 1584312NAS 1 1584348NAS 1 1584364NAS 1 1584620NAS 1 1584635NAS 1 1584665NAS 1 1585007NAS1 1585641NAS 1 1585642NAS 1 26 166092NAS 1 26 166093NAS1 26166448NAS 1 26166467NAS 1 26166480NAS 1 26166483NAS 1 26166485NAS 1 26 168051NAS 1 26170403NAS 1 26 172657NAS 26 172658NAS 26 172659NAS 26 3295NAS 26 3655NAS 26 3671NAS 26 3684NAS1 602017NAS 1 602116NAS 1 602120NAS 1 602142NAS 1 602171NAS 126 168124

NASA-CASE-LAR-12950 1

NASA-CASE-MFS-25842-1

NASA-CR-1 66092NASA-CR-166093NASA-CR-1 66448NASA-CR-166467NASA-CR-1 66480NASA-CR-1 66483NASA-CR-1 66485NASA-CR-1 68051NASA-CR-1 68 124NASA-CR-1 70403NASA-CR-1 72657NASA-CR-1 72658NASA-CR-1 72659NASA-CR-3295NASA-CR-3655NASA-CR-3671NASA-CR-3684

NASA-TM-82528NASA-TM-83069NASA-TM-83343NASA-TM-83349NASA-TM-83357NASA-TM-83370NASA-TM-83398NASA-TM-83411NASA-TM-84270NASA-TM-84305NASA-TM-84312NASA-TM-84348NASA-TM-84364NASA-TM-84620NASA-TM-84635NASA-TM-84665NASA-TM-85007NASA-TM-85641NASA-TM-85642

NASA-TP-2017NASA-TP-2116NASA-TP-2120NASA-TP-2142NASA-TP-2171

NAVTRAEQUIPC-81-0105-1

NTSB-AAR-83-01

ONERA, TPNO 1983-11ONERA, TP NO 1983-21ONERA. TPNO 1983-24

PB83-101659

p482p470p482p424p482p461p478p459p462p478p424p461p417p479p426p444p423p423p440p426p467p483p427p426p442p440p440p 440p442p427p427p424p424p424p427p458p459p478

p465

p477

p423p423p440p426p467p483p427p426p478p442p440p440p440p442p427p427p424

p470p423p458p482p470p482p424p482p461p478p459p462p478p424p461p417p479p426p444

p424p424p427p458p459

p466

p430

p464p480p464

p430

N83-266431

N83-25790'N83-27793'N83-25662*N83-27794'N83-26845'N83-27148'N83-26838'N83-26846'N83-27149'N83-25660'N83-26844'N83-26785'N83-27537'N83-26815'N83-25707'N83-25658'N83-25659'N83-25695'N83-26818'N83-26849'N83-27845'N83-26820'N83-26816'N83-26829'N83-25694'N83-25692'N83-25693'N83-26831 "N83-26822'N83-26819'N83-25667'N83-25665'N83-25666'N83-26821 'N83-25712'N83-26839'N83-27213'

N83-25727'

N83-26080'

N83-25658'N83-25659'N83-25695'N83-26818'N83-26849'N83-278451

N83-26820'N83-26816'N83-27213'N83-26829'N83-25694'N83-25692'N83-25693'N83-26831 'N83-26822'N83-26819'N83-25667'

N83-25854'N83-25657'N83-2571 1 'N83-266431

N83-25790'N83-27793'N83-25662'N83-27794'N83-26845'N83-27148'N83 26838'N83 26846'N8327149'N83-25660'N83-26844'N83-26785'N83-275371

N83-26815'N83-25707'

N83-25665'N83 25666'N83-26821 'N83 25712'N83-26839'

N83-25733

N83-26827

A83-36421A83-36430A83-36433

N83-25686

tttttttttttt#tttttttttttt#tttttttt#tttttttttttttttt###tt##tt#tttttt

#

tt

tt#tt##tt#tttttttttt#tttt#tt

#tttttttttttt#tt#ttittttttttttt#tt

#ttittttt

tt

tt

ttittt

#

E-2

REPORT NUMBER INDEX VPI-AERO-130

PB83-144865PB83 147413PB83-147751PB83-H8387PB83 910401

PNR-90159

PSU/TURBO-82-5

PWA-5?68-29

OTR-1 1QTR-12QTR-13

RADC-TR-82-253

RAE-LISRARY-TRANS-2087

RAND/N-1882-AF

REPT-761108/711129

RI/RD83-104

SAE PAPER 820955SAE PAPER 820956SAE PAPER 820957

SAND-8 1-0538

SER-510112-VOL-1

SWR 1-6800-129

TRANS-15857/TLT-00841

TRITA-FPT-042

UDR-TR 82-104

US-PATENT-APPL-SN-481 106US-PATENT-APPL-SN-489902

USAAEFA-80-07USAAEFA-80-17-2

USAAVRADCOM-TR-82-D-28USAAVRADCOM-TR-82-D-36USAAVRADCOM-TR-83-A-1

p460p479p471p475p430

p460

p427

p426

p440p440p440

p477

p426

p459

p471

p478

p433p433p434

p483

p42?

p471

p460

p460

p458

p465p477

p440p442

p477p429p478

N83-26843 #N83-27476 #N83-26934 ftN83-25919 #N83-26827 #

N83-26842 #

N83-26819' ft

N83-26816' ft

N83-25692' ftN83-25693- #N83-25694' #

N83-25990 #

N83-25677 #

N83-25714 ft

N83-26929 tf

N83-27213' #

A83-33627 #A83-33628' #A83-33629 #

N83-27803 #

N83-26820- #

N83-25904 #

N83-26842 #

N83-26843 #

N83-25713 #

N83-25727' #N83-26080' tf

N83-25698 #N83-25705 #

N83-26081 ftN83-25684 ftN83-27148' ft

VPI-AERO-130 p471 N83-27033 #

E-3

ACCESSION NUMBER INDEX


Typical Accession NumberIndex Listing

A83-11482 '# p 59

NASAACCESSION

NUMBER

r1NASA

DOCUMENTSYMBOL

T

MICROFICHESYMBOL

PAGENUMBER

Listings in this index are arranged alphanumencally byaccession number The page number listed to the rightindicates the page on which the citation is located An

asterisk (*) indicates that the item is a NASA report Apound sign (#) indicates that the item is available on

microfiche

A83-33486'A83-33487-A83-33505A83-33506'A83-33507A83-33545A83-33546A83-33548A83-33613A83-33621A83-33622A83-33625A83-33627A83-33628'A83-33629A83-33650A83-33767A83-33772A83-33900A83-33951A83-33952A83-33953A83-33954A83-33955A83-33964A83-33972'A83-33974A83-34170A83-34253A83-34311A83-34312A83-34315A83-34429A83-34472A83-34475A83-34500A83-34744A83-34849A83-34851A83-34852A83-34853A83-34854A83-34855A83-34858A83-34859A83-34860A83-34861A83-34862A83-34864A83-35039A83 35040A83-35052A83-35053A83-35054A83-35055

ttftttttftftttftftttftttttttftttttftttttftttttttttftttftftttttftttttftftftttftftttftftftttttttttftttftftttftft

p 481

p481

p482p433p472p428p433p 433p480p433p415p428p433p433p434p472p428p417p460p467p434p468p468p468p472p417p472p472p445p472p434p473p462p473p484p468p473p467p484p484p484p460p484p484p485p485p485p485p485p445p473p485p485p486p486

A83 35056A83-35057A83-35058A83-35059A83 35062A83-35087A83 35088A83 35089A83-35090A83-35121A83 35138A83 35192A83-35247A83-35273A83 35274A83-35275A83-35315A83 35535A83 35541A83-35590A83-35598A83 35599A83 35620A83-35623A83-35624A83 35625A83 35675A83-35707A83 35712A83 35772A83-35773A83-35790A83 35801A83-35806'A83-35809A83-35810A8335811A83-35812A83-35813A83 35820A83 35821AB3-35822A83-35828A83 35829A83-35830A83-35831A83-35832A83 35833A83-35838A83-35839A83 35841A83-35842'A83-35843 'A83 35846A83-35847

ftftttttftftttftttttttftftttftttftttttftttttftftttftttttttttttttttftttttttttftttftttftttftttttttttttftftftttft

p486p 486p486p 486p486p 430p430p430p431p460p434p431p468p431p431p431p434p 417p418p418p462p431p418p434p434p463p445p418p482p434p461p445p445p446P473p473p468p446p469p446p469p469p418p 446p446p446p446p447p418p418

p447p447p447p447p447

A83-35848 ttA83-35849 #A83-35850 ftA83-35852 #A83-35853 #A83-35854 ftA83-35856-0A83-35858 ttA83-358S9 #A83-35862 #A83-35863 ft

W\83-35865 ftA83-35866 ftA83-35868 ftA83-35869 #A83-35870 #A83-35871 ftA83-35872 ftA83-35873 ftA83-35874 ftA83-35875 ftA83-35879 ftA83-35880 #A83-35881 ftA83-35882 ftA83-35883'#A83-35933 #A83-35947 ftA83-35948'*A83-35949 ftA83-35950 ftA83-36039'#A83-36042' ftA83-36043' #A83-36046-1?A83-36065 ftA83-36066 ftA83-36073 #A83-36074 ifA83-36075 ftA83-36076' #A83-36077 #A83-36078 #A83-36085- #A83-36096'*A83-36122 ftA83-36166' ftA83-36174 #A83-36203 ftA83-36204 ftA83-36205 ftA83-36206 #A83-36207 ftA83-36210 ftA83-3621V ftA83-36212 ftA83-36214 ftA83-36215 ftA83-36216 ftA83-36217 ftA83-36218'#A83-36219 ftA83-36221 #A83-36222'#A83-36223 ftA83-36224 #A83-36225 #A83 36234 •#A83-36235' ftA83-36236 ftA83-36237 ftA83 36238 ftA83-36239'#A83-36240 #A83-36241 ftAB3 36243 ftA83-36244 ftA83-36250'*A83-36251 ftA83-36252'#A83-36253 #A83-36254 ftA83 36258 ft

p 447p 448p463p419p419p448p448p448p 448p473p463p448p448p 419p449p449p 449p449p419p419p419p449p 449p449p450p450p 474p435p435p435p435p474p428p428p419p435p469p463p435p435p420p482p420p474p482p431p469p474p415p436p436p436p443p480P436p480p436p437p463p463p463p463p474p464p480p464p437p437p420p450p474p450p474p469p469P470p450p450p451p451p451p451p420

A83-36259 ftA83 36260 ftAB3 36261 ftAS3-36277 • ftA83-36282 ftA83 36284 ftA83-36285-0A83-36286'*A83-36287'#A83 36291 ' ftA83 36292 ftA83 36293 ftA83-36294 ftA83-36295 ftA83 36296 ftA83-36297 ftA83-36298 ftA83-36299 ftA83 36300 ftA83 36301 ftA83-36302 ftA83-36303 ftA83-36304 ftA83363141 ftA83 36316' ftA83-36322 ftA83-36323'#A83-36324 ' ftA83 36325 ftA83-36326 ftA83-36327 ttA83-36328 ttA83 36329 ftA83-36339 ftA83-36340'#A83-36346 ftA83 36347 ftA83-36353'#A83-36354 ttA83-36355 ttA83 36356 ftA83-36357 ftA83-36363 ' ftA83-36364 ttA83 36365 #A83-36367 ftA83-36368 ftA83-36391 ' ttA83-36393 " ftA83-36394 ftA83-36395 ftA83-36396 #A83-36397 ttA83-36398 ttA83-36399 ttA83 36400 ftA83-36403 ttA83-36405 ftA83-36406' #A83-36408 " ftAB3-36409'*A83-36412 ttA83-36414 ftA83-36421 ftA83-36430 ftA83-36433 #A83-36443 ttA83-36448 ttA83-36450 ttA83-36455 ttA83-36457 ttA83-36458 ttA83-36459 ttA83-36460 ftA83-36461 ftA83-36462 ftA83-36463 #A83-36464 ttA83-36465 ttA83-36466 ftA83-36467 ftA83-36468 ftA83-36469 ft

p420p451p451p475p452p452p437p452p420p420p421p452p452p452p453p453p453p453p453p453p453p 444p 454p454p454p454p454p421p444p444p 444p455p455p455p455p455p455p464p475p421p464p455p421p421p421p456p456p422p456p456p456p456p457p457p467p457p422p475p437p467p422p457p422p464p480p464p415p437p422p480p415p415p415p437p438p438p457p457p 438p438p438p438p438

A83 36470 ftA83 36471 ftA83-36472 ftA83-36473 ttA83-36474 ftA83 36612 ttA83-36613 ttA83-36625 ttA83-36791 ttA83-36792 ttA83 36793 ftA83-36794 ftA83-36910 ttA83-36911 ttA83-36912 ttA83-36913 ttA83-36914 ftA83-36915 ttA83-36916 ttA83-36917 ttA83-36918 ttA83-36919 ttA83-36920 ftA83-36921 ttA83-36922 ttA83-36924 ftA83-36925 ttA83-36951 ttA83-36952 ttA83-36953 ttA83-36954 #A83-36960 tt

N83-25652 ttN83 25653 ttN83-25654 #N83-25655 ttN83-25656 ttN83-25657'#N83-25658'#N83-25659'#N83-256601*N83-25662'#N83-25665*#N83-25666" ttN83-256671*N83-25668 ttN83-25669 ttN83-25670 ttN83-25671 ttN83-25673 #N83-25674 ftN83-25675 ftN83-25676 ttN83-25677 ftN83-25679 ttN83-25682 ttN83-25683 ttN83-25684 ttN83-25685 ftN83-25686 ftN83-25687 #N83-25688 ttN83-25691 ttN83-25692'#N83-25693'#N83-25694'#N83-25695'*N83-25696 #N83-25697 ttN83-25698 ttN83-25699 ttN83-25700 ttN83-25701 ttN83-25702 ftN83-25703 ftN83-25704 #N83-25705 ftN83-25706 ttN83-25707-0N83-25709 ftN83-25710 #N83-2571V#

p432p416p439p439p439p457p 444P432P458p458p458p475p475p428p458p422p416p439p422p422p439p439p423p439p423p423p458p429p429p429p429p416

p416p416p416p416p417p423p423p423p424p424p424p424p424p424p424p425p425p425p425p425p425p426p426p426p429p429p430p430

-p432p432p432p 440p440p 440p440p 440p440p 440p441p441p441p 441p 441p 441p442p442p 444p444p445p45B

F-1

N83-25712 ACCESSION NUMBER INDEX

N83.25712-*N83-25713 ttN83-25714 #N8325715 ftN83-25716 ftN83-25717 #N83-25718 #N83-25719 ttN83 25720 ttN83 25721 #N83 25723 tfNB3 25725 #N83 25726 #N83 25727' #N83 25728 #N83 25730 #N83 25731 #N83 25732 ttN83 25733 #N83 25735 #N83.25790-0N83-25793 #N83-25795 #N83-25829 #N83-25854-#N83-25904 #N83-25919 #N83-25929 #N83-25934 ttN83-25935 #N83-25938 ifN83-25939 #N83 25948 ttN83-25990 #N83 26023 #N83 26080 '#N83 26081 ttN83-26099 #N83-26103 #N83-26320 #N83-26322 #N83-26345 #N83-26367 #N83-26501 #N83-26637 #N83-26643'*N83-26783 #N83-26785' #N83-26786 #N83-26787 #N83-26791 #N83-26792 #N83-26798 #N83-26805 #N83-26812 tfN83-26815'#N83-26816'#N83-26818'#N83-26819'#N83-268201 #N83 26821 • #N83-26822' #N83-26824 #N83-26825 #N83-26827 #N83-26828 #N83-26829'*N83-26830 #N83-26831 * ftN83-26832 ftN83-26833 #N83-26834 ttN83-26835 #N83-26836 #N83-26838'*N83-268391*N83-26840 #N83-26841 #N83-26842 #N83-26843 ttN83-26844' #N83-26845' #N83-268461 ttN83-26847 #N83-26848 ttN83-26849'#N83-26929 ttN83-26934 #N83-27033 ttN83-27034 #N83-27035 ttN83-27114 #N83-27148'#N83-27149' #N83-27210 ttN83-27213'#

p458p458p459p459p461p461p461p461p465p465p465p465p465p465p465p466p466p466p466p466p470p470p470p470p470p471p475p476p476p476p476p476p476p477p477p477p477p477p477p479p479p479p479p481p481p482p487p417p 417p417p459p466p459p477p442p426p426p426p427p427p427p427p427p428p430p432p442p442p442p 443p443p443p443p 443p459p459p459p460p460p460p461p461p462p462p462p467p471p471p471p471p471p478p478p478p478p478

N83-27260 ttN83-27476 ftN83 27537' ttN83-27624 #N83-27793- ttN83-27794' ttN83-27796 #N83-2780! ttN83-27803 ttN83-27845-*N83-27895 #N83-27921 tt

p478p479p479p481p482p482p483p483p483p483p483p487

F-2

1 Report NoNASA SP-7037(165)

2 Government Accession No 3 Recipient's Catalog No

4 Title and Subtitle

Aeronautical EngineeringA Continuing Bibliography (Supplement 16$)

5 Report DateSeptember 1983

6 Performing Organization Code

7 Author(s) 8 Performing Organization Report No

10 Work Unit No

9 Performing Organization Name and Address

National Aeronautics and Space AdministrationWashington D C. 20546

11 Contract or Grant No

13 Type of Report and Period Covered

12 Sponsoring Agency Name and Address

14 Sponsoring Agency Code

15 Supplementary Notes

16 Abstract

This bibliography lists 466 reports, articles and other documentsintroduced into the NASA scientific and technical informationsystem in August 1983

17 Key Words (Suggested by Author(s))

Aeronautical EngineeringAeronauticsBibliographies

18 Distribution Statement

Unclass i f ied - Unlimited

19 Security Classif (of this report)

Unclass if ied

20 Security Classif (of this page)

Unclassi f ied

21 No of Pages 22 Price*

HC

For sale by the National Technical Information Service, Springfield, Virginia 22161NASA-Lang!ey, 1983

NASA distributes its techn,ca' oocLrneiis and b'b'iogrsphic tools to eleven special Lb-anos 'ocaied m the organ?e-'IOPS 'istetj be'ow âc'i r j-s'y is p r3ae rpc .o fLi TSh :^3 public ELICP serv.ces as rs's's^cs assistance nte>"!i:reryloans, photocopy ss rv<ce anc ass.sls.ica in obtaining copiss of NASA documents for i-Sisntion

University of Call ornia 3srke ay

Jmvarsiiy o? Co oraoo 3o-.cs'

Library of Ccngrsss

Georgia Institute of Technology At'ariE

~i he uOm C'erar ibrary Ch caro

n/icssscnus3tts Institute of Technology, Carnbncgs

Lirde ,-'a I _ crary Manses C.Iy

Cc1 jmc'a U nvsrsny Me1 ' Yorkv / ^ , . ^ ^

University 01 Cklehorna Sixxall Libisry

Cci negis Liarsry of Piu

University o! Washington 3aaMa

NASA publications (.hose inc'icrinri by pn * following the accession number) are also received by -ns followingpublic ano free 'ib'c .es

Los Angeles Public LibrarySan Diego °ubiic -ibrary

Denver Public Lib.ary

Hartford Pub.'c -'o rary

Enoch Pratt Free _ib rery Baltimore

Boston Public Library

Detroit Public Library

Minneapolis Public Library and informationCenter

Trenton Public L brary

. ,3roo!dyn Public LibraryBuffalo and cr e Courty 3ublic ubreryRochester Public LibraryNeu' York Public Library

Akron Public LibraryCincinnati and Sarnilton County Public LibraryCleveland Publ.c Lib.aryDayton Public LibraryToledo and Lucas County ûblic Library

Dalles Pi-bl.c LibraryFort Worth Public Library

Seattle Public Libraryrvfj.»c;t:\s \Milwaukee ûb'ic Library

An extensive collection of NASA and NASA-sponsored documents and aerospace publications available to thspublic for reference purposes is maintained by the American Institute of Aeronautics and Astronautics Technicalinformation Service 555 West 57th Street 12th Floor New York New York 10019

An extensive collection of NASA and NASA-sponsored publications is maintained by the British Library LendingDivision Boston Spa Wetherby Yorkshire Eng.and By virtue of arrangements other than witn NASA, the BritishLibrary Lending Division also has available many of the non-NASA publications cited in STAR European requestersmay purchase facsimile copy of microfiche of NASA and NASA-sponsored documents those identified by boththe symbols * and * from ESA - Information Retrieval Service European Space Agency 8-10 rue Mario-Nikis,75738 Paris CEDEX 15 France

National Aeronautics andSpace Administration

Washington, D.C.20546

Official Business

Penalty for Private Use, $300

THIRD-CLASS BULK RATE Postage and Fees PaidNational Aeronautics andSpace AdministrationNASA-451

NASA POSTMASTER- 'f Unrtehverable (Section 158Postal Manual) Do Not Return