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NASA SP-7037(134)

AERONAUTICAL ENGINEERING

A Continuing Bibliography

Supplement 134

A selection of annotated references to unclas-sified reports and journal articles that wereintroduced into the NASA scientific and tech-nical information system and announced inMarch 1981 in

• Scientific and Technical AerospaceReports (STAR)

• International Aerospace Abstracts (IAA).

Scientific and Technical Information Branch 1 981National Aeronautics and Space Administration

Washington, DC

This supplement is available as NTISUB/141/093 from the National Technical InformationService (NTIS), Springfield. Virginia 22161 at the price of $5.00 domestic: $10.00 foreign.

INTRODUCTION

Under the terms of an interagency agreement with the Federal Aviation Administrationthis publication has been prepared by the National Aeronautics and Space Administrationfor the joint use of both agencies and the scientific and technical community concerned withthe field of aeronautical engineering. The first issue of this bibliography was published inSeptember 1970 and the first supplement in January 1971. Since that t ime, m o n t h l ysupplements have been issued.

This supp l emen t to Aeronautical Engineering - A Continuing Bibliography (NASASP-7037) lists 387 reports, journal articles, and other documents originally announced inMarch 1981 in Scientific and Technical Aerospace Reports (STAR) or in InternationalAerospace Abstracts (I A A).

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 in two major sections, IA AEntries and STAR Entries, in that order. The citations, and abstracts when available, arereproduced exactly as they appeared originally in IAA and STAR, including the originalaccession numbers from the respective announcement journals. This procedure, which savestime and money, accounts for the slight variation in citation appearances.

Three indexes -- subject, personal author, and contract number -- are included.An annual cumulative index will be published.

AVAILABILITY OF CITED PUBLICATIONS

IAA ENTRIES (A81-10000 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 S7.00 per document up to a maximum of 40 pages. The charge foreach additional page is $0.25. Microfiche of documents announced in IAA are available at therate of $3.00 per microfiche on demand, and at the rate of $1.25 per microfiche for standingorders for all IAA microfiche. The price for the IAA microfiche by category is available at the rateof $1.50 per microfiche plus a $1.00 service charge per category per issue. Microfiche of all thecurrent AIAA Meeting Papers are available on a standing order basis at the rate of $1.50 permicrofiche.

Minimum air-mail postage to foreign countries is $1.00 and all foreign orders are shipped onpayment of pro-forma invoices.

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

STAR ENTRIES (N81 10000 Series)

One or more sources from which a document announced in STAR is available to the public isordinarily given on the last line of the citation. The most commonly indicated sources and theiracronyms or abbreviations are listed below. If the publication is available from a source other thanthose listed, the publisher and his address will be displayed on the availability line or in combinationwith 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 followed by the letters HC or MF inthe STAR citation. Current values for the price codes are given in the tables on pageviii.

Documents on microfiche are designated by a pound sign (ft) 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 in Microfiche) isavailable at greatly reduced unit prices. For this service and for information concerningsubscription to NASA printed reports, consult the NTIS Subscription Section. Springfield.Va. 22161.

NOTE ON ORDERING DOCUMENTS: When ordering NASA publications (those followedby the * symbol), use the N accession number. NASA patent applications (only thespecifications are offered) should be ordered by the U S-Patent-Appl-SN number.Non-NASA publications (no asterisk) should be ordered by the AD. PB. or other reportnumber shown on the last line of the citation, not by the N accession number. It isalso 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, at the standard S3.50 price, forthose documents identified by a jf symbol.)

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

Avail: NASA Public Document Rooms. Documents so indicated may be examined at orpurchased from the National Aeronautics and Space Administration. Public DocumentsRoom (Room 126). 600 Independence Ave.. S.W.. Washington. D.C. 20546. or publicdocument rooms located at each of the NASA research centers, the NASA SpaceTechnology Laboratories, and the NASA Pasadena Office at the Jet PropulsionLaboratory.

Avail: DOE Depository Libraries. Organizations in U.S. cities and abroad that maintain collectionsof Department of Energy reports, usually in microfiche form, are listed in Energy ResearchAbstracts. Services available from the DOE and its depositories are described in abooklet. DOE Technical Information Center - Its Functions and Services (TID-4660).which may be obtained without charge from the DOE Technical Information Center.

Avail: Univ. Microfilms. Documents so indicated are dissertations selected from DissertationAbstracts and are sold by University Microfilms as xerographic copy (HC) and microfilm.All requests should cite the author and the Order Number as they appear in thecitation.

Avail: USGS. Originals of many reports from the U.S. Geological Survey, which may containcolor illustrations, or otherwise may not have the quality of illustrations preserved in themicrofiche or facsimile reproduction, may be examined by the public at the libraries ofthe USGS field offices whose addresses are listed in this introduction. The librariesmay be queried concerning the availability of specific documents and the possibleutilization of local copying services, such as color reproduction.

Avail: HMSO. Publications of Her Majesty's Stationery Office are sold in the U.S. by PendragonHouse, Inc. (PHI). Redwood City, California. The U.S. price (including a service andmailing charge) is given, or a conversion table may be obtained from PHI.

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

Avail: Fachinformationszentrum, Karlsruhe. Sold by the Fachinformationszentrum Energie, Physik,Mathematik GMBH, Eggenstein Leopoldshafen, Federal Republic of Germany, at the priceshown in deutschmarks (DM).

Avail: Issuing Activity, or Corporate Author, or no indication of availability. Inquiries as to theavailability of these documents should be addressed to the organization shown in thecitation as the corporate author of the document.

Avail: U.S. Patent and Trademark Office. Sold by Commissioner of Patents and Trademarks.U.S. Patent and Trademark Office, at the standard price of 50 cents each, 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 in combinationwith the corporate author line.

GENERAL AVAILABILITY

All publications abstracted in this bibliography are available to the public through the sourcesas indicated in the STAR Entries and IAA Entries sections. It is suggested that the bibliographyuser contact his own library or other local libraries prior to ordering any publication inasmuch asmany of the documents have been widely distributed by the issuing agencies, especially NASA.A listing of public collections of NASA documents is included on the inside back cover.

SUBSCRIPTION AVAILABILITY

This publication is available on subscription from the National Technical Information Service(NTIS). The annual subscription rate for the monthly supplements is $50.00 domestic; $100.00foreign. All questions relating to the subscriptions should be referred to NTIS. Ann: Subscrip-tions. 5285 Port Royal Road. Springfield Virginia 22161.

VI

ADDRESSES OF ORGANIZATIONS

American Institute of Aeronauticsand Astronautics

Technical Information Service555 West 57th Street. 1 2th FloorNew York. New York 10019

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

Commissioner of Patents andTrademarks

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

National Technical Information Service5285 Port Royal RoadSpringfield. Virginia 22161

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

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

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

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

Fachinformationszentrum Energie, Physik,Mathematik GMBH

7514 Eggenstein LeopoldshafenFederal Republic of Germany

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

NASA Scientific and Technical InformationFacility

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

National Aeronautics and SpaceAdministration

Scientific and Technical InformationBranch (NST-41)

Washington, D.C. 20546

University MicrofilmsA Xerox Company300 North Zeeb RoadAnn Arbor, Michigan 48106

University Microfilms, Ltd.Tylers GreenLondon. England

U.S. Geological Survey1033 General Services Administration

BuildingWashington. D.C. 20242

U.S. Geological Survey601 E. Cedar AvenueFlagstaff, Arizona 86002

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

U.S. Geological SurveyBldg. 25, Denver Federal CenterDenver, Colorado 80225

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TABLE OF CONTENTSIAA Entries 99STAR Entries 125

Subject Index .-. A-1Personal Author Index B-1Contract Number Index C-1

TYPICAL CITATION AND ABSTRACT FROM STAR

NASA SPONSOREDDOCUMENT

NASA ACCESSIONNUMBER

-» N81-1063«*# FWG Associates. Inc.. Tullahoma. Tenn.-.-

- AVAILABLE ONMICROFICHE

TITLE-

r

AUTHORS-

CONTRACTOR GRANT-

REPORTNUMBER-

PILOT-AIRCRAFT SYSTEM REPONSE TO WIND SHEARInterim ReportBarry S. Turkel and Walter Frost Washington NASA Nov.-1980 98 p refs(Contract NAS8-33458) _,(NASA-CR-3342) Avail: NTIS^ HC A05/MF A01 CSCL04B*

The nonlinear aircraft motion and automatic control modelis expanded to incorporate the human pilot into simulations ofaircraft response to wind to wind shear. The human pilot isdescribed by a constant gains lag filter. Two runs are carriedout using pilot transfer functions. Fixed-stick, autopilot, andmanned computer simulations are made with an aircraft havingcharacteristics of a small commuter type aircraft flown throughlongitudinal winds measured by a Doppler radar beamed alongthe glide slope. Simulations are also made flying an aircraftthrough sinusoidal head wind and tail wind shears at the phugoidfrequency to evaluate the response of manned aircraft inthunderstorm wind environments. S.F.

-CORPORATESOURCE

-PUBLICATIONDATE

-AVAILABILITYSOURCE

-COSATICODE

TYPICAL CITATION AND ABSTRACT FROM IAA

AIAA ACCESSIONNUMBER

TITLE-

TITLE OFPERIODICAL-

I' A81-10474 tt ^The design of blowing-cooled aircraft electrical

machines (Voprosy konstruktsii produvaemykh aviatsionnykh elek-tricheskikh mashin). V. I. Naumenko, O. G. Klochkov, and V. V. .Bandurin (Akademiia Nauk Ukrainskoi SSR, Institut Elektrodina-miki, Kiev, Ukrainian SSR). Tekbnicheskaia Elektrodinamika, July-

~AVAILABLE ONMICROFICHE

'AUTHORS

Aug. 1980, p. 81-87. In Prussian.The current status of air-cooled aircraft electrical machines is

reviewed. The possibility of reducing the weight and size ofair-cooled machines is discussed, with particular emphasis on thedesign of cooling systems for synchronous ac-generators. B.J.

AUTHOR'SAFFILIATION

-PUBLICATIONDATE

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V-f

AERONAUTICALENGINEERING A Continuing Bibliography (Suppl. 134)

APRIL 1981

IAA ENTRIES

A81-16551 ff Steady flow past a rectangular wing withcirculation that is variable along the span (Statsionarnoe obtekaniepriamougol'nogo kryla s tsirkuliatsiei peremennoi po razmakhu). N.N. Poliakhov and Z. N. Shesternina. Leningradskii Universitet,Vestnik, Matematika, Mekhanika, Astronomiia, July 1980, p. 85-92.In Russian.

A method is proposed for solving the problem of the steadyflow past a plane rectangular wing at low angle of attack with anarbitrary distribution of circulation along the span. The spanwisedistribution of density of attached vortices is prescribed in the formof a power series with indefinite coefficients; this makes it possibleto carry out integration along the span in quadratures and todetermine series coefficients from the condition that circulation atthe ends of the wing is equal to zero. Series coefficients are solutionsof a system of Fredholm equations of the second kind. B.J.

A81-16578 The implications of current flight controlresearch and development. R. C. Ettinger (USAF, Flight DynamicsLaboratory, Wright-Patterson AFB, Ohio). (Society of ExperimentalTest Pilots, Symposium, 24th, Beverly Hills, Calif., Sept. 24-27,1980.) Society of Experimental Test Pilots, Technical Review, vol.15, no. 2, 1980, p. 18-37.

The impact of current flight control research and developmenton present and future aircraft is considered. Attention is given to thedevelopment of such systems as fly-by-wire, tactical weaponsdelivery, DIGITAC, control configured vehicle, integrated flight firecontrol, mission adaptive wing, and wing-in-ground effect. B.J.

A81-16579 F/A-18 full scale development test. W. H.Brinks (McDonnell Douglas Corp., St. Louis, Mo.). (Society ofExperimental Test Pilots, Symposium, 24th, Beverly Hills, Calif.,Sept. 24-27, 1980.) Society of Experimental Test Pilots, TechnicalReview, vol. 15, no. 2, 1980, p. 38-46.

The flight envelope of the F/A-18 in the fighter escortconfiguration (two AIM-7s, two AIM-9s, and a 20-mm gun) has beenexpanded to 1.9 Mach number in flutter testing, and to zero airspeedduring high angle of attack maneuvers. Flutter testing has beencompleted for the fighter escort configuration with the required 15%or better flutter margin and damping at the most critical flightcondition. During high angle of attack testing the aircraft has beenflown in dynamic maneuvers to over 90-deg angle of attack and35-deg of sideslip with no departure tendencies in the fighter escortconfiguration. The load factor envelope has been expanded to anegative 2.8 gs and a positive 7.6 gs at various speeds and altitudes.

B.J.

A81-16580 Advanced Attack Helicopter /YAH-64/ - Sta-tus report. J. W. Groulx (Hughes Helicopters, Culver City, Calif.).(Society of Experimental Test Pilots, Symposium, 24th, BeverlyHills, Calif., Sept. 24-27, 1980.) Society of Experimental Test Pilots,

Technical Review, vol. 15, no. 2, 1980, p. 47-58.The Advanced Attack Helicopter (YAH-64) is designed primari-

ly as an antiarmor helicopter capable of operating day or night in thenap-of-the-earth environment. This paper provides an aircraft descrip-tion, and gives attention to the status of test vehicles, flight testresults, and ordnance testing. B.J.

A81-16581 * Shipboard trials of the Quiet Snort-Haul Re-search Aircraft /QSRA/. J. L. Martin (NASA, Ames Research Center,Moffett Field, Calif.) and P. B. Strickland (U.S. Navy, Naval Air TestCenter, Patuxent River, Md.). (Society of Experimental Test Pilots,Symposium, 24th, Beverly Hills, Calif., Sept. 24-27, J980.1 Societyof Experimental Test Pilots, Technical Review, vol. 15, no. 2, 1980,

p. 59-74. 6 refs.The feasibility of the application of advanced state-of-the-art

high lift STOL aircraft in the aircraft carrier environment wasevaluated using the NASA Quiet Short-Haul Research Aircraft(QSRA). The QSRA made repeated unarrested landings and freedeck takeoffs from the USS Kitty Hawk while being flown by threepilots of significant different backgrounds. The exercise demonstrat-ed that the USB propulsive lift technology presents no unusualproblems in the aircraft carrier environment. Optimum parametersfor landing the QSRA were determined from the shore-basedprogram; these proved satisfactory during operations aboard ship.Correlation of shipboard experience with shore-based data indicatesthat both free deck takeoffs and unarrested landings could beconducted with zero to 35 knots of wind across the deck of anaircraft carrier the size of the USS Kitty Hawk. B.J.

A81-16582 Head-Up-Display flight tests. S. J. Monaganand R. E. Smith (Calspan Advanced Technology Center, Buffalo,N.Y.). (Society of Experimental Test Pilots, Symposium, 24th,Beverly Hills, Calif., Sept. 24-27, 1980.) Society of ExperimentalTest Pilots, Technical Review, vol. 15, no. 2, 1980, p. 75-87.

HUD flight tests conducted for the United States Navy and AirForce by the Flight Research Branch of the Calspan AdvancedTechnology Center are described. The HUD flight test systemincludes the NT-33A variable fly-by-wire research aircraft, a program-mable HUD, and a workload assessment device. The integration ofthe Display Evaluation Flight Test System and the workloadassessment device with the NT-33 in-flight simulation aircraft hasresulted in an advanced systems research aircraft for USAF and USNflight research. This aircraft has proved to be a powerful tool forinvestigating the relationships between displays, flying qualities, andpilot performance and workload. B.J.

A81-16583 Air traffic management enhancement throughnew avionics /4-D/. D. A. Moor (Lockheed Corp., Burbank, Calif.).(Society of Experimental Test Pilots, Symposium, 24th, BeverlyHills, Calif., Sept. 24-27, 1980.) Society of Experimental Test Pilots,Technical Review, vol. 15, no. 2, 1980, p. 90-93.

The first phase of a NASA/Lockheed program for the 1980s isto expand the current L-1011 Flight Management System descentmode to include the fourth dimension, time. This would enable an

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A81-16584

L-1011 to make a completely automatic descent (4-D) from cruisealtitude to arrive at a metering fix within a few seconds of a timeallocated by ATC. The initial 4-D descent flight tests of theprototype system were such that a 2sigma arrival time errordisposition of 8 sec is believed to be an attainable goal. B.J.

A81-16584 757/767 design considerations for improvedproductivity. T. E. Twiggs (Boeing Commercial Airplane Co., Seattle,Wash.). (Society of Experimental Test Pilots, Symposium, 24th,Beverly Hills, Calif., Sept. 24-27, 1980.1 Society of ExperimentalTest Pilots, Technical Review, vol. 15, no. 2, 1980, p. 94-113. 7 refs.

In the fall of 1981 and the spring of 1982, flight testing isscheduled to begin on a new series of technology transports, the 757and the 767. Productivity improvement will be extracted fromvarious disciplines of the aircraft design; among the technologiescontributing are weight savings, aerodynamic efficiency, digitalelectronic reliability and adaptability, and improved cockpit environ-ment. These factors are reviewed along with pilot workloadmodification, descent strategies, and ATC compatibility. B.J.

A81-16585 A cockpit view of advanced airline avionics. R.F. Hanna (American Airlines, Inc., Dallas, Tex.). (Society ofExperimental Test Pilots, Symposium, 24th, Beverly Hi/Is,,Calif.,Sept. 24-27, 1980.1 Society of Experimental Test Pilots, TechnicalReview, vol. 15, no. 2. 1980, p. 114-134.

Several current and proposed future developments in advancedairline avionics are described. Particular-consideration is given to theARINC Communications Addressing and Reporting System, theElectronic Flight Instrument System, and the Engine Indicating andCrew Alerting System. It is suggested that advanced airline avionicswill provide: (1) enhanced safety by reducing head downtime and byproviding more timely crew alerting, (2) increased passenger comfortby providing better enroute weather update for optimum routeselection, (3) better on-time performance through maintenancemonitoring for corrective action and dispatch, and (4) improved fuelefficiency by displaying real-time performance and navigation datafor more effective management. B.J.

A81-16586 The future ATC system as influenced byadvanced avionics, S. I. Rothschild (FAA, Washington, D.C.).(Society of Experimental Test Pilots, Symposium, 24th, BeverlyHills, Calif., Sept. 24-27, 1980.1 Society of Experimental Test Pilots,Technical Review, vol. 15, no. 2, 1980, p. 135-145.

The paper describes current FAA activities underway to attemptto determine how the future ATC system should evolve and how thefeatures provided by that future system should tie into near-termdevelopments. Attention is given to activities dealing with nationalflow planning, the terminal area, navigation, air-ground communica-tions, human factors, and weather. B.J.

A81-16587 Development and certification of the Gulf-stream III. R. K. Smyth (Grumman Aerospace Corp., Bethpage,N.Y.). (Society of Experimental Test Pilots, Symposium, 24th,Beverly Hills, Calif., Sept. 24-27, 1980.) Society of ExperimentalTest Pilots, Technical Review, vol. 15, no. 2, 1980, p. 155-167.

The paper discusses the development and certification testing ofGrumman's new business jet, the Gulfstream III. The G-lll representsan improved version over its predecessor, the G-ll, with a longerfuselage, a modern recontoured nose, and a new wing to which hasbeen added NASA winglets to control wing-tip airflow and reducedrag due to lift. These new features give the G-lll a 4600 Ib increasein fuel capacity and increase its range to 3600 nautical miles. Duringpreliminary test flights a phenomenon known as 'aileron tug'occurred as a function of Mach number and lift coefficient causingthe need for installation of a row of vortex generators forward of theailerons. On its first transoceanic flight from Savannah to Hannover,the G-lll exhibited no problems and in subsequent tests includingminimum unstick speed and high speed upset maneuvers, metcertification requirements. B.R.K.

A81-16588 * The XV-15 tilt rotor research aircraft. D. C.Dugan (NASA, Ames Research Center, Moffett Field, Calif.), R. G.Erhart (Bell Helicopter Textron, Fort Worth, Tex.), and L. G.Schroers (U.S. Army, Aeromechanics Laboratory, Moffett Field,Calif.). (Society of Experimental Test Pilots, Symposium, 24th,Beverly Hills, Calif., Sept. 24-27, 1980.) Society of ExperimentalTest Pilots, Technical Review, vol. 15, no. 2, 1980, p. 168-185.

The XV-15 tilt rotor has shown good handling qualities in allmodes of flight; in the helicopter mode it allows precision hover andagility with low pilot workload. Vibration and noise levels are low;the conversion procedure is easy, with satisfactory acceleration ordeceleration. The XV-15 handling demonstrated its potential formany civil and military applications. A.T.

A81-16684 Sarsat - A rescue system for ships and aircraft(SARSAT • ein Rettungssystem fur Schiffe und Flugzeuge). J. Nauck(Erno Raumfahrttechnik GmbH, Bremen, West Germany). Nach-richten Elektronik, vol. 34, Oct. 1980, p. 362-364. In German.

The Sarsat satellite is discussed along with alternative orbit plansfor ocean and general emergence services. Emphasis is placed ondesigning an economical system. A system of satellites in geostation-ary orbit employs 3 satellites and covers 94% of the earth surface. Asystem of 8 satellites in polar orbits provides 100% coverage of theearth. A system of satellites in geostationary and polar orbits is alsoexamined which overcomes the advantages of the individual system.A proposal using quasi-polar orbits recommended by IMCO (Inter-governmental Maritime Consultative Organization) is illustrated andcompared to a plan with a 57 degree orbit. R.C.

A81 -16688 A new system for the study of visual informa-tion presentation in aeronautics - GIBI (Un nouveau systeme d'etudede la presentation d'informations visuelles en aeronautique - LeGIBI). J. P. Menu, G. F. Santucci, and C. L. Valot. MedecineAeronautique et Spatiale, Medecine Subaquatique et Hyperbare, vol.19, 3rd Quarter, 1980, p. 185-187. In French.

The GIBI (French acronym for interactive binary image genera-tor) system to be used in the development of electronic cockpitdisplays as well as in fundamental research on visual perception ispresented. The system makes use of cathode ray tube imagesgenerated by a calculator-based information system operating in realtime through either a shadow mask or a penetration rider scanninggraphics processor, and is capable of reacting to subject responses. Itmay be used in flight simulations to determine the essentialparameters for piloting at each stage of the flight and a usefulsymbology in which this information may appear. A.L.W.

A81-16689 Helicopter alarms - The use of ALAT incidentand accident record cards (Les alarmes en helicopters - Exploitationdes fiches d'incidents et d'accidents de I'A.L.A.T.). J. P. Papin and B.Gangloff. Me'decine Aeronautique et Spatiale, Medecine Sub-aquatique et Hyperbare, vol. 19, 3rd Quarter, 1980, p. 188-190. InFrench.

Records of helicopter accidents and incidents kept by ALAT areanalyzed in order to determine the roles played by on-board alarms.The causes, diagnostic procedures, and crew reactions to 262incidents on various types of helicopters over several years areexamined. It is pointed out that diagnosis is more often immediatewhen the cause is mechanical and when an alarm is functioning, andthat when the diagnosis is immediate, the action taken is most oftenadequate. It is concluded that an improvement in the presentation ofalarms may increase flight safety, particularly as regards thedetermination of the cause of the situation and the utilization ofsignals. A.L.W.

A81-16712 Sound radiation from a finite length unflangedcircular duct with uniform axial flow. I - Theoretical analysis. II -Computed radiation characteristics. G. W. Johnston and K. Ogimoto(Toronto, University, Toronto, Canada). Acoustical Society ofAmerica, Journal, vol. 68, Dec. 1980, p. 1858-1883. 23 refs. Natural

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A81-17044

Sciences and Engineering Research Council of Canada Grant No.A-7945.

An analysis of sound radiation from a finite length, unflanged,hard wall circular duct with uniform axial flow using the Wiener-Hopf method is presented. The acoustic model simulates the noiseradiation from a turbojet aircraft engine in flight at low and mediumthrust levels as in landing or steady cruise flights. It includes thediffraction of sound at both ends and its mean convection by theduct and external flow fields; the refraction effects resulting fromnonuniform exterior flow fields at the inlet and exhaust under highthrust conditions are not included. The finite duct effects arequantitatively presented for the case of plane-excitation; the finiteduct radiation has length resonance which produces standing waveson either side of the source plane. The diffracted sound wavesinterfere in the farfield resulting in a modified radiation directivityrelative to the semi-infinite duct radiation. AT.

A81-16717 il A case study in aircraft design: The deHavilland family of STOL commuter aircraft. R. D. Hiscocks. NewYork, American Institute of Aeronautics and Astronautics, Inc.,1980. 129 p. 19refs.$15.

The development of de Havilland STOL commuter aircraft fromDHC-1 Chipmunk through the DHC-6 Twin Otter is described.Special attention is then given to the development of the DHC-7;preliminary design considerations, aircraft weight, noise, structuralphilosophy, construction materials, qualification testing, the power-plant, engine mounts, propulsion control, and lateral control, aredescribed. Finally, attention is given to the current market for STOLcommuter aircraft, and to plans for the DHC-8. B.J.

A81-16718 ii Concorde aerodynamics and associated sys-tems development. J. Rech (Societe Nationale Industrielle Aero-spatiale, Toulouse, France) and C. S. Leyman (British Aerospace,Bristol, England). New York, American Institute of Aeronautics andAstronautics, Inc., 1980. 104 p. S15.

A case study on the innovative aspects of Concorde aerodynam-ics is presented. Attention is given to design objectives, aircraftaerodynamic layout, flying qualities, performance and noise, andpowerplant aerodynamics. B.J.

A81-16719 ;/' A case study on the F-16 fly-by-wire flightcontrol system. C. S. Droste and J. E. Walker. New York, AmericanInstitute of Aeronautics and Astronautics, Inc., 1980. 120 p. $15.

The implementation of the F-16 fly-by-wire system is describedwith emphasis on the electrical-to-mechanical interface (i.e., theYF-16 control surface actuation system), redundancy, and lightningprotection. The unique flight control system functional features arethen discussed, with attention given to AOA/g limiting, high-AOAroll coordination, roll rate limiter, rudder fadeout, yaw rate limiter,and manual pitch override. B.J.

A81-16720 ;/' The Grumman Aerospace and GulfstreamAmerican Gulfstream III case study in aircraft design. L. M. Mead(Grumman Aerospace Corp., Bethpage, N.Y.), Ch. Coppi (GulfstreamAmerican Corp., Van Nuys, Calif.), and J. Strakosch (GrummanAerospace Corp., Bethpage, N.Y.). New York, American Institute ofAeronautics and Astronautics, Inc., 1980. 115 p. S15.

A design evaluation of the Gulfstream III executive jet ispresented. Attention is given to the ancestry of Gulfstream III andrequirements definition, preliminary design studies and the evolutionof the Gulfstream III design, and a design description and thedevelopment program of Gulfstream III. B.J.

A81 -16721 II The Gossamer Condor and Albatross: A casestudy in aircraft design. J. D. Burke (AeroVironment, Inc., Pasadena,Calif.). New York, American Institute of Aeronautics and Astro-nautics, Inc., 1980. 66 p. 20 refs. (AV-R-80/540) S15.

The design and testing of the Gossamer Condor and theGossamer Albatross, the first human-powered aircraft to completethe figure-eight course required for the Kremer prize and to cross the

English Channel, respectively, are discussed as an example of anindividual entrepreneurial approach to aircraft design. The objectivesand guiding principles of the design program are outlined, and the

sequence of project events is traced from the time of the firstconception of a low-velocity man-powered aircraft in 1976 to thecross-channel flight of the Gossamer Albatross in June, 1979.Aircraft performance and aerodynamic design are examined, withattention given to the available and required power, and theevolution of aircraft stability and control. Aircraft structures andinstrumentation are discussed, and the way in which all the necessarydevelopments came together in the successful flight of the GossamerAlbatross despite turbulence and headwinds is related. A.L.W.

A81-16939 ;/' Renewal function for any arbitrary period - ABayesian way. D. D. Bhattacharya (Ministry of Defence, Directorateof Scientific Evaluation, New Delhi, India). Defence Science Journal,vol. 30, Jan. 1980, p. 17-20. 6 refs.

The usual format on which the consumption data and activityfor spare parts of a system are available, makes it difficult for theevaluation of the renewal function on the procedure as laid down byCox (1967). The author has, therefore, discussed in this paper amodel through Bayesian Approach as to how in such cases therenewal function could be obtained for any period of activity,provided the past experiences are available in the form of a sampleinformation. For a Beta-Prior density for the mean demand rate ofthe Poisson demand distribution, the renewal function in itsanalytical and asymptotic forms are obtained. (Author)

A81-16968 H Inverse problems of controlled flight dynamics- Longitudinal motion (Obratnye zadachi dinamiki upravliaemogopoleta - Prodol'noe dvizhenie). B. N. Petrov and P. D. Krut'ko(Moskovskoe Vysshee Tekhnicheskoe Uchilishche, Moscow, USSR).Akademiia Nauk SSSR, Doklady, vol. 255, no. 1, 1980, p. 43-47. InRussian.

The paper deals with the development of a new approach to theconstruction of aircraft control algorithms. The approach is basedessentially on the concept of inverse problems of dynamics,introduced by Petrov, Krut'ko, and Popov (1979). The basic aspectsof automatic aircraft control are analyzed on the basis of a nonlinearmathematical model whose equations are written in a system ofvelocity coordinates. V.P.

A81 -16969 # The method of superelements in the dynamicsof complex structures (Metod superelementov v dinamike slozhnykhstruktur). I. F. Obraztsov, A. S. Vol'mir, and V. N. Terskikh(Voenno-Vozdushnaia Inzhenernaia Akademiia, Moscow, USSR).Akademiia Nauk SSSR, Doklady, vol. 255, no. 1, 1980, p. 59-61. InRussian.

The paper deals with the superelement method, as an extensionof the finite element method, capable of treating complex systemswith very high computer speed and memory requirements. Thecoupling of superelements of different orders is demonstrated, usinga delta wing configuration as an example. The normal mode vibrationfrequencies of the fuselage and four wing sections are plotted andcompared with the experiment. V.P.

A81-17044 H Airline flight departure procedures • Choosingbetween noise abatement, minimum fuel consumption and minimumcost. R. E. Jones. Canadian Aeronautics and Space Journal, vol. 26,3rd Quarter, 1980, p. 181-199. 13 refs.

A performance computer program was developed to analyzereduced noise takeoff procedures for the B-737 and B-747 aircraft.The I ATA procedure was quieter by 5 dB within 10 nm of theairport (where noise levels are highest) than the more fuel efficientATA method which uses 80 Ib less of fuel in a B-737 and 450 Ib lessin the B-747. The operational cost of a B-747 using the ATA methodfor full-power takeoff is higher because of greater maintenancecharges; a decision basis is proposed for the B-747 which uses IATAprocedures for heavyweight takeoffs and ATA recommendations forlightweight takeoffs. A.T.

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A81-17045 H Productivity - The challenge of aircraft andengine maintenance. P. E. Benham (CP Air, Richmond, BritishColumbia, Canada). (Canadian Aeronautics and Space Institute,Annual General Meeting, Vancouver, Canada, May 13, 1980.)Canadian Aeronautics and Space Journal, vol. 26, 3rd Quarter, 1980,p. 201-208. 7 refs.

Several methods of improving maintenance in aircraft operationswhich should produce the most reliable components at lowest costsare explored. The aims of aircraft maintenance include serviceableequipment, on-time flight departures, and higher scheduled aircraftutilization; these goals are limited by high maintenance costs,requirements for low fuel consumption, and limited ground supportcapital investment. A successful productivity manufacturing contractnegotiated by Canadair and the Internal Association of Machinistsand Aerospace Workers was based on relating work compensationand bonuses to schedule improvements and production planning; thismethod is difficult to apply in airline maintenance because ofunexpected failures and nonroutine types of repair. A computersystem for engine planning was developed which comprises a file ofcomponent specifications, an on-line video terminal which displaysall repairs required, and a computer terminal which reviews theschedule and priorities. A.T.

A81-17046 // Today and the future in aircraft wheel andbrake development. J. P. Ruppe (Bendix Corp., Aircraft Brake andStrut Div., South Bend, Ind.). (Canadian Aeronautics and SpaceInstitute, Annual General Meeting, Vancouver, Canada, May 13,1980.) Canadian Aeronautics and Space Journal, vol. 26, 3rdQuarter, 1980, p. 209-216.

A review of developments in aircraft wheel and brake design forcommercial aviation which emphasizes low weight, longer life, andsafety is presented. Modern wheels designed by computer modelswhich simulate stresses from tire contact forces, deflections, andstrains are discussed, along with thermal analyses of the wheel andbrake assemblies. Wheel materials are usually 2014-T6 or T61 forgedaluminum, but Ti, composites, and powder metallurgy Al alloys arebeing considered as alternates. An aircraft brake was also designed bycomputer simulation to produce a lightweight failure-resistantcomponent; the most significant advance in brake design wasapplication of steel/ceramet antifriction compositions with increasedbrake life. It is concluded that future aircraft brakes will be made ofcarbon composites of greater wear resistance, high heat storagecapacity, and strength maintained at elevated temperatures. A.T.

A81-17047 # Optimum selection of main parameters for thereverse design of a supersonic military aircraft. T. S. Patel (IndianInstitute of Technology, Bombay, India) and C. S. Dixit (Air India,Bombay, India). Canadian Aeronautics and Space Journal, vol. 26,3rd Quarter, 1980, p. 218-229. 8 refs.

Reverse design problem of developing supersonic militaryaircraft around a given engine has been dealt with in the presentpaper. Optimum selection of the main parameters has been carriedout for the airplane performing specified mission requirements. Twovariants are worked out using two different criteria of evaluation; (1)minimum fuel requirements; and (2) maximum payload capacity.The feasible direction method of M. J. Box for nonlinear constrainedoptimization has been used in preparing computer software. Theprogram developed can be easily modified to incorporate changes inconstraints, addition of constraints or changes in objective function.The final results obtained are compared with the geometry of atypical military airplane of the same type and power plant. (Author)

A81-17048 # Transonic axisymmetric bodies with minimalwave drag. Y. Y. Chan, D. J. Jones (National Research Council, HighSpeed Aerodynamics Laboratory, Ottawa, Canada), and D. L.Mundie. Canadian Aeronautics and Space Journal, vol. 26, 3rdQuarter, 1980, p. 231-234. 10 refs.

An optimization technique was applied in the design of areadistributions of transport aircraft with minimum wave drag at hightransonic speeds. The minimal drag bodies were calculated for the

Mach number range of 0.98-1.10. Below this range, the shock is tooweak to affect the drag; at subsonic flows above this Mach range, theflow over a slender body is described up to the first order by thelinear supersonic theory, achieving the minimal wave drag body ofSears-Haack. It was concluded that axisymmetric bodies withminimal wave drag at near-sonic speeds can be designed by numericaloptimization techniques using a finite difference code for the flowfield computation. At subsonic Mach numbers, the optimum bodyhas a blunt nose and an almost shockless condition. A.T.

A81-17049 # Application of fracture mechanics in designinglower wing skin of transport aircraft. V. G. Nanduri (De HavillandAircraft of Canada, Ltd., Downsview, Ontario, Canada). CanadianAeronautics and Space Journal, vol. 26, 3rd Quarter, 1980, p.235-238.

An application finite element method of using fracture mechan-ics in the design of test panels similar to the lower surface of atransport aircraft wing is discussed. The cracked stiffened panel isassumed to be a composite material with the skin and stiffenersrepresenting the matrix and fibers; an expression is derived for thenet section stress to produce total panel failure. The expression isbased on the law of mixtures equation, the notch strength analysis ofKuhn (1967), and the proportional limit of the stress-strain curve asthe limiting stress for the stiffeners. Detail designs of a wing bottomsurface and of the narrow 7- and 6-stringer panels are presented; thefailure of a 7-stringer panel during a residual strength test isphotographically depicted. A.T.

A81-17067 Periodically stiffened fluid-loaded plates. I -Response to convected harmonic pressure and free wave propagation.II - Response to line and point forces. B. R. Mace (Southampton,University, Southampton, England). Journal of Sound and Vibration,vol. 73, Dec. 22, 1980, p. 473-504. 17 refs. Research supported bythe Ministry of Defence (Procurement Executive).

A formulation for the vibration and sound radiation offluid-loaded plates periodically stiffened by line supports is presentedfor line and point force excitations. The response to a convectedharmonic pressure is determined by Fourier transforms; at lowfrequencies, where the separation of the stiffeners is less thanone-third of the plate wavelength, the stiffened plate behaves like anequivalent orthotropic plate. At higher frequencies, the inputmobility shows peaks at specific frequencies which can be identifiedwith the bounding frequencies of zero propagation zones, andstanding waves can be set up on the plate. With further increases infrequency, the mobility approaches a value determined by theproperties of the structure at the point of excitation. A.T.

A81-17143 /?' Fuel conservation in the air transportationindustry - General and operational aspects (II contenimento delconsume di carburante nell'industria del trasporto aereo - Aspettigenerali ed operativi). A. Schiavo. Ingegneria, Sept.-Oct. 1980, p.257-266. 8 refs. In Italian.

A81-17146 H Aerodynamic design of a ducted propeller -Optimization of efficiency (II progetto aerodinamico di un'elicaintubata - Ottimizzazione del rendimento). S. de Ponte and A. Baron(Milano, Politecnico, Milan, Italy). Ingegneria, Sept.-Oct. 1980, p.273-278. In Italian.

A81-17166 H Rolls-Royce engines status report. AircraftEngineering, vol. 52, Dec. 1980, p. 2-7.

The article presents a survey of various Rolls-Royce enginesincluding RB211 Turbofan, Pegasus Vectored-Thrust Turbofan,Olympus 593 Turbojet, Dart Turboprop, RB 401 Demonstrator andBusiness Jet Engine, Viper Turbojet, Tyne Turboprop, ConwayTurbofan, Gnome Turboshaft Engine, and Turmo III C4. All of theengines have undergone extensive testing and are reviewed for theirindividual features. The RB211 Turbofan models have a take-offthrust of about 50,000 Ib and improved fuel consumption and have

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been used in the Lockheed L. 1011-1 Tristar, and the Boeing 747.The RB211-535, being developed for the new Boeing 757 twinjetairliner is discussed together with the Adour Turbofan model whichpowers the Anglo-French Jaguar supersonic strike/trainer aircraft.The latter has a take-off thrust of 5,115 Ib. for the Adour Mk. 102and of 5,700 Ib for the Adour -56. The major feature of theseengines is a significant increase in reheat thrust. The Olympus 593Turbo-jet has a take-off thrust of 38,000 Ib and is the mostextensively tested commercial engine. The Dart Turboprop is along-serving commercial gas turbine noted for its fuel economy andlow noise levels. Finally the Gem Turboshaft Engine which powersthe twin engine Westland Lynx helicopter has a fuel consumptionsignificantly better than similar engines in service. B.R.K.

A81-17167 ,*' Coatings in the aero gas turbine. R. H. Wedgeand A. V. Eaves (Rolls-Royce, Ltd., Aero Div., Bristol, England).Aircraft Engineering, vol. 52, Dec. 1980, p. 25-29.

The paper discusses sprayed coatings for gas turbine engines, thedifferent problems associated with different parts of the engine, andfuture developments in the use of sprayed coatings and their likelyimpact on cost effectiveness within the gas turbine industry. Thetraditional metallic coatings such as 'hard' chrome to produce wearresistance, copper and tin as soft metals associated with bearings,cadmium plating for corrosion resistance, and silver plating foranti-seize/anti-fret application are supplemented by 'sprayed' coat-ings. The major problems which can arise in gas turbine engines arehammer wear (combatted by chromium plating or various plasmasprayed carbide coatings), fretting and rubbing wear (combatted bycopper-nickel-indium, copper-nickel, aluminum bronze, and alumi-num bronze-polyester}, rotating seal problems (combatted bysprayed alumina), and high temperatures (combatted by variousnickel-chromium alloy sprays). A table is given which shows thevarious sprayed coatings and their cost effectiveness. Future develop-ments are anticipated in the method of application and componentsof the various sprayed coatings. B.R.K.

A81-17324 # Turbopropeller engine P2L-10S. W. Kordzin-ski. Technika Lotnicza i Astronautyczna, vol. 35, May 1980, p. 10,11. In English and Polish.

The paper deals with the design, specifications, and performanceof a version of the Soviet TWD-10 turboprop engine currentlymanufactured in Poland on the basis of a license agreement. Theengine is intended for the An-28 STOL aircraft and the PZL Sokolhelicopter. Modern time and labor saving methods used in theproduction of the engine are noted. V.P.

A81-17325 /' The PZL-Sokol - New Polish helicopter. T.Chwalczyk. Technika Lotnicza i Astronautyczna, vol. 35, May 1980,p. 33-37. In English and Polish.

The medium-weight-class helicopter under consideration fitsbetween the Soviet helicopters, Mi-2 and Mi-8, as a substitution ofthe Mi-4, whose production has been terminated. In the passengerversion of the helicopter, 12 (removable) seats are arranged in a1.4-m high 3.2 x 1.56 m cabin. The design characteristics andspecifications of the helicopter are examined. V.P.

A81-17371 ;! Comparative evaluation of the quality of jetfuels (Sravnitel'naia otsenka urovnia kachestva reaktivnykh topliv).A. F. Gorenkov. Khimiia i Tekhnologiia Topliv i Masel, no. 12, 1980,p. 21-25. 5 refs. In Russian.

A methodology is presented for comprehensive evaluation offuel products which involves (1) selection of the base values ofquality indices, (2) determination of the relative values of qualityindices by establishing a functional relationship between the actualand the base value of each index, (3) determination of the weightsfor each of the relative quality indices, and (4) calculation of thecombined quality index. Evaluation results are given for several fuelgrades. V.L.

A81-17372 ;/' Formation of solid phase during the heating ofjet fuels (Osobennosti obrazovaniia tverdoi fazy pri nagreve reaktiv-nykh topliv). V. V. Malyshev and V. A. Astaf'ev. Khimiia iTekhnologiia Topliv i Masel, no. 12, 1980, p. 25-27. 10 refs. InRussian.

The mechanisms of tar and sludge formation during thermaloxidation of jet fuels have been investigated under static anddynamic conditions in the temperature range 120-200 C. It is foundthat tar deposits consist of high-molecular compounds whosesolubility and adsorption properties change with increasing tempera-ture by nonoxidation mechanisms. These compounds are thought tocause the coagulation of the solid phase. Under static conditions,sludge formation is largely determined by the surface oxidation ofthe fuel. V.L.

A81-17373 H Composition of sludge formed in B-3V oil(Sostav osadkov, obrazuiushchikhsia v masle B-3V). E. A. Kunina, V.G. Kuznetsov, G. T. Novosartov, and L. V. Boiko. Khimiia iTekhnologiia Topliv i Masel, no. 12, 1980, p. 27-29. In Russian.

The composition of sludge which precipitates from B-3V oil andis deposited on oil filters and other components of the lubricatingsystems of gas turbine engines has been investigated by chemical andIR spectral analyses. It is found that filter deposits are formed byAltax, an oxidation product of the antiscoring additive Captax, whilethe deposits formed on the hottest components of the system consistmostly of additive oxidation products and oxides of the metals ofthe structural components. To reduce the deposits, it is recommend-ed to increase the thermal oxidation stability of B-3V oil by meansof more effective antioxidation additives. V.L.

A81-17375 tt Joint-laboratory qualification testing of oilsfor gas turbine engines (Mezhlaboratornye ispytaniia masel dlia GTDpo metodam kvalifikatsionnoi otsenki). R. R. Bureeva, S. E. Krein,and G. T. Novosartov. Khimiia i Tekhnologiia Topliv i Masel, no. 12,1980, p. 41-43. 12 refs. In Russian.

Data on the kinematic viscosity, lubricating properties, andthermal oxidation stability of several aviation oils based on testresults from five different laboratories have been statisticallyevaluated for convergence and repeatability using the method ofdispersion analysis. Indices of convergence and repeatability areshown to be useful tools for evaluating the accuracy of test methodsused. V.L.

A81-17453 Captive carry and free flight rain erosionconsiderations for reinforced ablative fluorocarbon radome materials.G. F. Schmitt, Jr. (USAF, Materials Laboratory, Wright-PattersonAFB, Ohio). SAMPE Journal, vol. 16, Nov.-Dec. 1980, p. 12-16. 6refs.

Experiments were conducted to assess the rain erosion behaviorduring captive carry and free flight of reinforced ablative plasticsused in missile radomes. Forty-eight specimens were mounted onboth the left and right sides of a supersonic rain erosion wedge with12 each at the following angles: 13.5, 30, 45, 60 deg and then testedon a Holloman rocket sled track 50,000 feet long with 18,000 feetequipped with nozzles for rain simulation at speeds up to Mach 4.0(4200 fps). The principal materials variables investigated were typesof polymer (polytetrafluoroethylene, fluorinated ethylene propyl-ene, polyfluoroalcohol, ethyltetrafluoroethylene), type of reinforce-ment (S-glass, E-glass, AB-312 aluminum borosilicate), amount offiber loading (10 to 40 percent by weight), and orientation of fibers(perpendicular to surface, parallel to surface, random). Some of theconclusions show that the fiber reinforced fluorocarbon plasticswhich exhibited the lowest mean-depth-of-penetration at 60 degwere also the best at the 13.5 deg angle; the polytetrafluoroethyleneand polyfluoroalcohol fluorocarbon polymers provide the besterosion resistance; and the aerodynamic heating of supersonic freeflight in combination with erosion conditions at Mach 4.0 change therankings of ablative fluorocarbons compared to erosion resistance atsubsonic velocities. B.R.K.

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A81-17467 Problems of flight mechanics involved in all-weather helicopter operation (Flugmechanische Probleme bei derRealisierung des Allwettereinsatzes von Hubschraubern). P. Hameland B. Gmelin (Deutsche Forschungs- und Versuchsanstalt fiir Luft-und Raumfahrt, Institut fiir Flugmechanik, Braunschweig, WestGermany). Zeitschrift fur Flugwissenschaften und Weltraum-forschung, vol. 4, Nov.-Dec. 1980, p. 335-345. 12 refs. In German.

In view of the inferior flight mechanical behavior of thehelicopter, in particular, with respect to military all-weather require-ments, some major factors influencing the flight mechanical behaviorof the pilot/helicopter system are examined. Flight mechanicalproblem areas are elucidated, and the basic flight properties of thehelicopter that would enable all-weather operation are discussed.Methods of optimizing basic helicopter flight characteristics areproposed. V.P.

A81-17471 The effect of aerodynamic coupling on thedynamics of aircraft in fast rolling motion (Einfluss der aerodyna-mischen Kopplung auf die Flugzeugdynamik bei schnellen Rollbewegungen). G. Sachs and W. Fohrer (Miinchen, Hochschule derBundeswehr, Neubiberg, West Germany). Zeitschrift fur Flugwissen-schaften und Weltraumforschung, vol. 4, Nov.-Dec. 1980, p.379-388. 28 refs. In German.

The paper deals with the effects of coupling of longitudinal andlateral aerodynamic characteristics on the dynamics of rollingaircraft. The aerodynamic coupling considered is caused by unsym-metric flow conditions resulting from sideslipping where rollingmoments due to angle-of-attack and pitching moments due to angleof sideslip are of particular significance for the problem addressed. Itis shown that the attainable rate of roll is significantly influenced andthat marked effects on stability are possible. Furthermore, it isshown that aerodynamic coupling can cause au tor o tat ion (i.e., arolling motion without aileron forcing moments). The results arederived using simplified relations and complete six-degree-of-freedomcalculations. (Author)

A81-17472 A wall interference analysis (Zur Ermittlungvon Wandinterferenzen). J. Barche. Zeitschrift fur Flugwissenschaf-

•ten und Weltraumforschung, vol. 4, Nov.-Dec. 1980, p. 389-396. 6refs. In German.

In the present paper, an attempt is made to apply theoreticalexperience to the problem of correcting for the wall effect in windtunnels. A method based on Green's theorem is proposed, in whichcorrection for the wall effect is made from the interference signalsgenerated by a body situated in the proximity of the wall. Because ofthis location, the body itself does not figure in the calculations. Theonly requirement of the method is that the flow be attached at thewall (i.e., that the interference field may be described by potentialtheory). V.P.

A81-17488 The effect of cyclic loading on the apparentcleavage fracture toughness of 1Cr-Mo-V rotor steel. I. Roman, K.Ono (California. University, Los Angeles, Calif.), and A. S. Tetelman.Engineering Fracture Mechanics, vol. 14, no. 1, 1981, p. 155-159,161-163. 19 refs. Research supported by the Electric Power ResearchInstitute.

A significant increase in the cleavage fracture toughness of1Cr-Mo-V rotor steel due to cyclic loading was observed. A newmodel that is capable of predicting and explaining the observation isproposed. The model combines macroscopic fracture criteria withthe assumption that transient flow properties of a material in thecyclic plastic zone can be represented by those of the materialsubjected to macroscopic low cycle fatigue under fully reversedstrain control. (Author)

A81-17501 Specialists' Meeting on Helicopter PropulsionSystems, Williamsburg, Va., November 6-8, 1979, Technical Papers.Meeting sponsored by the American Helicopter Society. Washington,D.C., American Helicopter Society, 1980. 239 p. $18.

The meeting focused on engine technology, drive systems,propulsion system operations, and propulsion systems integration.Papers were presented on contingency ratings, digital control forhelicopter powerplants, the T700 booster stage, advanced transmis-sion component development and test program, safety considerationsfor drive train design, survey of propulsion system failures resultingin mishaps, failure indication and corrective action for turboshaftengines, and an infrared suppressor for the Black .Hawk helicopter.

A.T.

A81-17502 The impact of contingency ratings on ad-vanced turboshaft engine design. A. Brooks (General Electric Co.,Lynn, Mass.). In: Specialists' Meeting on Helicopter PropulsionSystems, Williamsburg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society,1980. 7 p.

An aircraft engine designer's consideration of contingencypower ratings of advanced turboshaft engines is presented. It wasshown that one engine inoperative requires methods of achievingshort time horsepower (SHP) increments of 10-20%; large increasesin SHP (above 20%) for contingency power will be limited bycompressor capability and local high temperatures leading to hotsection hardware failures. A.T.

A81-17503 A simple combustor system for a small gasturbine engine. G. Opdyke, Jr. and B. C. Forbes (Avco Corp., AvcoLycoming Stratford Div., Stratford, Conn.). In: Specialists' Meetingon Helicopter Propulsion Systems, Williamsburg, Va., November 6-8,1979, Technical Papers. Washington, D.C., Amer-ican Helicopter Society, 1980. 9 p. 12 refs.

The design of a simple, low cost annular combustor, based on aunique aerodynamic mixing concept, is described in terms of itsmechanical simplicity, versatility in the use of different fuel injectionsystems, and its demonstrated performance characteristics. Thedesign, called a circumferentially stirred combustor, incorporates aprimary zone flame stabilization method which results in aninexpensive shape for the combustor liner and a reduction of thenumber of fuel injectors to about one half that normally used for aswirl stabilized annular primary zone design. This circumferentiallystirred combustor design has been applied to helicopter enginemodels and to advanced shaft and fan engines. (Author)

A81-17504 Digital control for helicopter powerplants. D.A. Caine (Lucas Industries, Inc., Lucas Aerospace Div., Englewood,N.J.) and S. Janik (Avco Corp., Avco Lycoming Stratford Div.,Stratford, Conn.). In: Specialists' Meeting on Helicopter PropulsionSystems, Williamsburg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society,1980. 16 p.

Full-authority electronic control of helicopter engines usingdigital large scale integration technology is described. The controluses a 12-bit complementary metal-oxide semiconductor micro-processor as a compromise between the 8-bit and 16-bit systems,requiring low electrical power consumption. The software logic, theinterfacing of the digital system with the powerplant and theairframe by optical serial links, and self-diagnostics methods arediscussed. A.T.

A81-17505 The digital control system as part of anintegrated accessory fit for future engines. M. P. Perks and T. G.Morton (Rolls-Royce, Ltd., Aero Div., Leavesden, Herts., England).In: Specialists' Meeting on Helicopter Propulsion Systems, Williams-burg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society, 1980. 12 p.The paper suggests that the traditional approach of designing the

control system in isolation from the other accessories on a gasturbine engine may not provide the most cost effective total solutionfor an engine having a digital control system. It is considered that theintegrity of the digital control can be maintained while providingadditional functions not associated with its prime control task. This

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could allow the development of advanced monitoring systems tominimize life cycle costs and achieve maximum aircraft utilization.The application of these principles to helicopter engines is discussedand an arrangement proposed which could provide substantialbenefits both to the helicopter pilot and to the ground crew. Pilotworkload would be substantially reduced by advising him of engineor aircraft management factors on a 'need to know' basis. Operatorswould benefit from regular information on the operational status ofthe engines. (Author)

A81-17506 The T700 booster engine. A. Brooks (GeneralElectric Co., Lynn, Mass.). In: Specialists' Meeting on HelicopterPropulsion Systems, Williamsburg, Va., November 6-8, 1979, Techni-cal Papers. Washington, D.C., American Helicop-ter Society, 1980. 7 p.

The T700 booster engine which provides greater horsepower byusing a high tip speed transonic axial compressor combined with amoderate pressure ratio centrifugal compressor resulting in high ratioand engine efficiency is described. The engine RDT&E costs werelow; the problem of matching the discharge flow of the constant rpmbooster stage with the variable flow requirement of the core enginecompressor is discussed. AT.

A81-17507 Advanced transmission component develop-ment and test program. P. C. FitzGerald and G. F. Gardner (UnitedTechnologies Corp., Sikorsky Aircraft Div., Stratford, Conn.). In:Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg,Va., November 6-8, 1979, Technical Papers.Washington, D.C., American Helicopter Society, 1980. 14 p.

The Advanced Transmission Components Investigation Programfor future helicopters is analyzing stainless steel fabricated maintransmission housings, advanced thrust carrying cylindrical rollerbearings, and a high contact ratio buttress tooth form gear made of anew CBS 600 low alloy steel. High temperature gearbox operationwill be designed to eliminate the oil cooler; a finite element modelwas used to determine stainless steel housing thicknesses and the ribstructure for the crash load design criteria. A.T.

A81-17508 Drive system development for the 1980's. J.W. Lenski, Jr. and J. C. Mack (Boeing Vertol Co., Philadelphia, Pa.).In: Specialists' Meeting on Helicopter Propulsion Systems, Williams-burg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society, 1980. 12 p. 9refs. Army-sponsored research.

The design and testing of advanced helicopter transmissioncomponents including high-speed tapered roller bearings, integratedbearings and gears, high-speed seals, and high-modulus compositegear housings are described. Integral-shaft inner races are beingdeveloped for high speed bearings, and means of improving internaloil flow for greater tolerance to oil interruption are designed. Theassembly weight, number of bearings, faying surfaces, oil flow rates,and equipment test life are compared for current and advancedtransmission systems. A.T.

A81-17509 Development of helicopter transmission com-ponents for the 1980s. R. A. Battles (Bell Helicopter Textron, FortWorth, Tex.). In: Specialists' Meeting on Helicopter PropulsionSystems, Williamsburg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society,1980. 8 p. 9 refs. Army-supported research.

New components and materials are being evaluated for applica-tion to the next generation of helicopter transmissions. Three typesof involute gears • standard spur, high contact ratio (HCR) spur, anddouble-helical (D-H) - are to be evaluated in direct comparison tests.These tests will evaluate the following parameters: noise, efficiency,scoring, pitting, bending, and loss-of-lubricant operation. The testprogram is not to be concluded until early 1981; however, calculatedtest results are discussed. All three types of gears are made ofCarpenter EX-00053, a new, high-temper-resistant, air-hardening,carburizing steel. The double-helical sun and planet gears are made inone piece by shaping, shaving, carburizing, and honing. In conjunc-

tion with the gear tests, three rolling bearing materials, AMS 6444(CEVM 52100), AMS 6491 (DVM M-50), and silicon nitride will becompared. Additionally, an input spiral bevel pinion with integralball bearing inner races and a minilube system will be evaluated.

(Author)

A81-17510 Safety considerations for helicopter drivesystems of the 1980s. H. Ferris (FAA, Los Angeles, Calif.). In:Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg,Va., November 6-8, 1979, Technical Papers.Washington, D.C., American Helicopter Society, 1980. 8 p.

The impact of helicopter drive systems on safety is reviewed.Problems included the inability to estimate drive system loads,incorrect dynamic analysis for fatigue, failure to design for fatigue byminimizing stress raisers, and inadequate lubrication and cooling.Recommendations are made for manufacturing and testing of gears,bearings, seals, fasteners, housings, couplings, and driveshafts. A.T.

A81-17511 Helicopter propulsion system developmentand qualification. V. R. Edwards (U.S. Army, Propulsion and PowerDiv., St. Louis, Mo.). In: Specialists' Meeting on Helicopter Propul-sion Systems, Williamsburg, Va., November 6-8, 1979, TechnicalPapers. Washington, D.C., American HelicopterSociety, 1980. 8 p. 5 refs.

The U.S. Army programs for developing helicopter propulsionsystems and relating them to the total aircraft weapon arrangementare described. Turbine engines provided large reductions in weightand their turboshaft systems reduced fuel consumption; a newspecification included requirements for polar moments of inertia,torsional spring constants, sand and dust ingestion, and provisions forlow cycle fatigue and stress rupture. The airframe design handbookspecifies engine circumferential design limits, rotor blades, andfast-acting control devices for rapid aircraft maneuvers. A.T.

A81-17512 Development and operational flight test of themodel 250-C28B gas turbine engine. F. J. Schweibold (GeneralMotors Corp., Detroit Diesel Allison Div., Indianapolis, Ind.). In:Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg,Va., November 6-8, 1979, Technical Papers.Washington, D.C., American Helicopter Society, 1980. 8 p.

The development and flight testing of the 250-C28B gas turbineengine installed in a 206L1 helicopter are described. The tests weremade for initial engine/drive train stability, response characteristics,compressor surge margins, water/snow ingestion capabilities, andrelight system operation. Mission endurance profiles were establishedalong with requirements for air bleeds, ground and air starts, andfull-authority electronic fuel controls. A.T.

A81-17513 A survey of propulsion systems' malfunc-tions/failures resulting in helicopter mishaps. L. T. Burrows (U.S.Army, Applied Technology Laboratory, Fort Eustis, Va.). In:Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg,Va., November 6-8, 1979, Technical Papers.Washington, D.C., American Helicopter Society, 1980. 6 p.

A survey of propulsion systems malfunctions/failures (M/F) wasbased on the record of four Army helicopter models during1971-1978. The analysis included power plants, power transmissions,lubrication, fuel, and instrumentation; the tail rotor gearbox, theintermediate/combiner gearbox, and drive shafting were evaluated inthe power train subsystems. Component M/F histories relating tohelicopter mishaps are presented, noting that relatively insignificantcomponents have been a continuing cause of mishaps. M/F occur-rence can be reduced by proper design and manufacturing practices,together with adequate maintenance during the life of the helicopter.

A.T.

A81-17514 Issues regarding Army turboshaft enginesdiagnostics and condition monitoring. G. W. Hogg (U.S. Army,Applied Technology Laboratory, Fort Eustis, Va.). In: Specialists'

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Meeting on Helicopter Propulsion Systems, Williamsburg, Va.,November 6-8, 1979, Technical Papers. Washing-ton, D.C., American Helicopter Society, 1980. 15 p.

A review of Army helicopter diagnostic methods, conditionmonitoring equipment, and turboshaft engine maintenance ispresented. Engine maintenance by modules detects malfunctions,providing leadtime for repair and reducing secondary damage; itproduces data for life-limited hardware tracking, determines opera-tional readiness, and enhances safety. Technological improvementshave been utilized in engine gas path determinations, oil monitoring,vibration signature analysis, and application of electronic micro-miniaturization for analyzing and displaying diagnostic data. A.T.

A81-17515 Failure Indication and Corrective Action forturboshaft engines. A. D. Pisano (General Electric Co., AircraftEngine Group, Lynn, Mass.). In: Specialists' Meeting on HelicopterPropulsion Systems, Williamsburg, Va., November 6-8, 1979, Techni-cal Papers. Washington, D.C., American Helicop-ter Society, 1980. 10 p.

In order to prevent loss of power modulation capability in theevent of a failed engine control sensor, an automatic in-flight FailureIndication and Corrective Action (PICA) strategy is developed foradvanced turboshaft helicopter applications. PICA provides for boththe detection of a failed sensor and the generation of the bestestimate of the failed signal which can then be used to providecontinuity of stable engine control. The technical basis of PICA is aconstant gain extended Kalman filter. The PICA structure consists ofa nonlinear model of the turboshaft engine along with update logicto force the model to track the actual engine behavior. Utilizing theresults of extensive computer simulations with an advanced turbo-shaft engine, the T700-GE-700, it is shown that stable engine controlcan be maintained in the presence of multiple sensor failures.

(Author)

A81-17516 Review of engine/airframe/drive train dynamicinterface development problems. W. J. Twomey (United Tech-nologies Corp., Sikorsky Aircraft Div., Stratford, Conn.). In:Specialists' Meeting on Helicopter Propulsion Systems, Williamsburg,Va., November 6-8, 1979, Technical Papers.Washington, D.C., American Helicopter Society, 1980. 11 p. 6 refs.Grant No. DAAJ02-77-C-0037.

The coupled interaction between two or more helicoptersubsystems has often been the source of vibration problems. Thispaper gives a review of Sikorsky experience with such problems overthe past twenty years of developing gas turbine powered helicopters.This review is part of an overall Government effort to accumulatedata which will eventually lead to solutions of generic problems ofthis type. The problems presented include forced vibration problems,self-excited vibrations, and a transient response problem. Eighteenproblems are sumarized and grouped according to type. Five of theproblems are described in some detail. Recent trends in problems arediscussed. Recommendations are made for future analytical/testingefforts to achieve an improved understanding of interfacing dynamicproblems and potential solutions. (Author)

A81-17517 Engine-airframe transient compatibility -Analysis and test. J. R. Alwang (Boeing Vertol Co., Philadelphia,Pa.). In: Specialists' Meeting on Helicopter Propulsion Systems,Williamsburg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society, 1980.9 P.

This paper discusses dynamic analysis and test requirementsrelated to engine-airframe compatibility in two areas: drive systemtorsional stability and transient response. Prediction of stabilitycharacteristics using linear techniques and correlation with experi-mental data are reviewed. Control testing, leading to determinationof worst-case conditions, is presented with an aircraft flight testprocedure for providing an accurate evaluation of propulsion systemstability. The importance of developing a nonlinear component-by-component engine simulation for optimizing control functionalconfigurations and transient schedules is emphasized. Use of a

dynamic simulation based on steady state matching deck perfor-mance for analyzing specific interface problems, including transientloss in compressor surge margin, is demonstrated. (Author)

A81-17518 Is the engine helicopter-worthy. A. G. Attridge(Bell Helicopter Textron, Power Plant Design Group, Fort Worth,Tex.). In: Specialists' Meeting on Helicopter Propulsion Systems,Williamsburg, Va., November 6-8, 1979, Technical Papers.

Washington, D.C., American Helicopter Society, 1980.9 p.

Is the engine helicopter-worthy is a question posed mostfrequently at the beginning of every new design program. This paperdiscusses some of the difficulties encountered in the installation ofthe engine in terms of effects on airframe hardware. The BellHelicopter Textron Models 214A and 214ST are used as examples ofcurrent single- and twin-engine technology. (Author)

A81-17519 Advanced technology turboshaft IR suppres-sion. F. Husted (U.S. Navy, Naval Air Propulsion Center, Trenton,N.J.), J. F. Hurley, and J. N. Dale (Avco Corp., Avco LycomingStratford Div., Stratford, Conn.). In: Specialists' Meeting on Helicop-ter Propulsion Systems, Williamsburg, Va., November 6-8, 1979,Technical Papers. Washington, D.C., AmericanHelicopter Society, 1980. 8 p.

The development and testing of a passive IR suppression systemfor an advanced technology turboshaft engine are described. Theexhaust plume gas radiation and exhaust ducting hot metal radiationwere analyzed for all aspect and zenith angles; engine power losseswere minimized by a suppressor feature which permits full powerrecovery in permissive flight zones. The suppressor utilizes turbineexhaust gas energy to pump plume dilution and wall cooling air; amaximum plume and hot metal radiation suppression is providedwith a minimum power loss by a rectangular vane-vane configuration.Power loss data are presented in terms of increased back pressure onthe engine, and metal skin temperatures are given in the form ofmetal cooling effectiveness. A.T.

A81-17520 General Electric infrared suppressors for theBlack Hawk helicopter. M. C. Harrold (General Electric Co., AircraftEngine Group, Lynn, Mass.). In: Specialists' Meeting on HelicopterPropulsion Systems, Williamsburg, Va., November 6-8, 1979, Tech-nical Papers. Washington, D.C., American Heli-copter Society, 1980. 14 p.

A cruise operation infrared (IR) suppressor has been used inBlack Hawk helicopter propulsion systems to counter heat-seekingmissiles. The design includes suppressor core, transition duct, nacelleram inlet, rear seals, and inlet particle ducting system; they operateon ram pressure in forward IR signature for a cruise velocity of 4000ft altitude, 95 F ambient temperature, with a 9-hp maximumhorsepower loss per engine over an unsuppressed engine configura-tion. . A.T.

A81-17521 Exhaust gas reingestion measurements. B.Turczeniuk (Boeing Vertol Co., Philadelphia, Pa.). In: Specialists'Meeting on Helicopter Propulsion Systems, Williamsburg, Va.,November 6-8, 1979, Technical Papers. Washing-ton, D.C., American Helicopter Society, 1980. 12 p.

Results of flight tests to measure the magnitude and effects ofengine exhaust gas reingestion and inlet pressure distortion arepresented. The tandem rotor CH-47 and single rotor YUH-61Ahelicopters were flown with instrumented engine inlets usingfast-response probes. A wide range of flight maneuvers wereevaluated, including operating in and out of ground effect, flares,hovering turns, lateral and rearward flight. The dynamic inlet airtemperature and pressure patterns, time histories, and variation ofbasic engine parameters during exhaust reingestion are provided. Theeffect of instrumentation time constant on the maximum inlettemperature rise is discussed. Also shown is the effect of an inletscreen on pressure distortion. Conclusions are drawn as to the use ofthis data to establish turbine engine compressor stall margin

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requirements needed to avoid experiencing problems with theengine/helicopter integration. (Author)

A81-17522 ft The supercritical profile of the supercriticalwing (Superkritische Profile - Superkritische Fliigel). O. Wagner(Miinchen, Technische Universitat, Munich, West Germany). Luft-und Raumfahrt, vol. 1, 4th Quarter, 1980, p. 105, 106, 108, 109. 10refs. In German.

This paper discusses the profile wing design for supercriticalstructures. Emphasis is placed on the flow of air surrounding thewing and variations in flow fields are examined. Modifications to theprofile for flight below transonic levels are presented that increasethe uplift pressure and permit the achievement of critical Machnumbers on the order of 0.85. The uplift pressure along the upperside of the profile is compared for a classical and a Peaky profile. Acomparison of classical and supercritical wing cross sections indicatesa flatter upper side, a larger nose radius, and a thicker profile to thesupercritical wing. R.C.

A81-17525 ti Aerial surveying of small areas from a smallremotely controlled drone (Aerofotos'emka malykh uchastkov sdistantsionno upravliaemogo bespilotnogo mini-nositelia). A. G.Vanin. Geodeziia i Kartografiia, Nov. 1980, p. 55-58. In Russian.

Some aspects of the automation of aerial surveying arediscussed. Data obtained in West Germany with radio-controlledmodel aircraft and helicopter, using a 6 by 6 cm photogrammetriccamera are examined. V.P.

A81-17656 Laminar boundary layer on swept-back wingsof infinite span at an angle of attack. I. G. Brykina, E. A. Gershbein,and S. V. Peigin. (Akademiia Nauk SSSR, Izvestiia, MekhanikaZhidkosti i Gaza, May-June 1980, p. 27-39.) Fluid Dynamics, vol.15, no. 3, Nov. 1980, p. 344-354. 24 refs. Translation.

In the present paper, the compressible boundary layer flow onswept wings of infinite span is studied for various angles of attackunder the assumption of an impermeable or BLC wing surface. Afirst-approximation analytical solution is obtained (also for axisym-metric flow) by an integral method of successive approximations.Asymptotic solutions of the boundary layer equations are obtainedfor large values of the BLC parameter. V.P.

A81-17735 ,4 Experimental investigations on shock-associated noise. D. Ma, P. Li, G. Dai, and H. Wang (Academia Sinica,Acoustics Institute, Peking, Communist China). Sc/entia Sinica, vol.23, Oct. 1980, p. 1237-1246. 13 refs.

Shock-associated noise from a choked airjet produces soundfields and spectra which vary widely with different nozzles andpressure ratios between 2 and 8. The overall sound pressure levels inthe direction perpendicular to the jet show deviations of the soundpressure level from turbulent noise at the ratio of 2, rising to 20 dBat ratios above 3, and then remaining constant up to the ratio of 8.5.Expressions are derived for screech frequency and peak frequency ofwide-band shock-associated noise which agree with experimentaldata; significant dips are observed in the frequency spectra of acomposite jet noise at a specific pressure ratio which results from aninterference effect between wide-band and turbulent noises. A.T.

A81-17548 ft One-dimensional considerations concerningthe stability behavior of inlet diffusers for supersonic aircraft(Eindimensionale Betrachtungen zum Stabilitatsverhalten von Ein-laufdiffusoren fur Qberschall-Flugantriebe). H.-L. Weinreich. Darm-stadt, Technische Hochschule, Fachbereich Maschinenbau, Dr.-Ing.Dissertation, 1979. 192 p. 77 refs. In German.

The thesis deals essentially with the nonlinear interactionbetween inlet and diffuser in the case of frictionless flow in a longconnecting channel. Under the assumption that the inlet length ismuch smaller than the total length, it is shown that isolated buzzcycles can appear even below the stability boundary if throttling istoo nonuniform, while regular (normal) pulsations set in when acertain throttle level is exceeded. The transient process leads swiftlyto a well-established cycle. Throttling just above the stable inter-action boundary gives rise to vigorous pulsations. V.P.

A81-17577 If Principle for the design of hybrid controlsystems for passenger transport systems (Printeip postroeniia gibrid-nykh sistem upravleniia passazhirsko-transportnykh samoletov). I. A.Mikhalev and B. N. Okoemov. Priborostroenie, vol. 23, Oct. 1980, p.45-50. In Russian.

Methods for the design of onboard hybrid control and process-ing systems for passenger aircraft are described. The hybrid automat-ic control system is designed as a quasi-continuous system whosecharacteristics are close to those of an initial optimal continuoussystem. The aircraft control algorithm is constructed on the basis ofa law for the control of continuous systems, which are synthesizedby a method of optimal continuous linear systems. P.T.H.

A81-17622 Stationary displacement of a body by a shockwave. E. I. Zababakhin and IM. E. Zababakhin. (PMTF - ZhurnalPrikladnoi Mekhaniki i Tekhnicheskoi Fiziki, Mar.-Apr. 1980, p.135-137.) Journal of Applied Mechanics and Technical Physics, vol.21, no. 2, Sept. 1980, p. 269, 270. Translation.

The conditions where a streamlined body will travel togetherwith a shock front, on which it floats like a cork in water, areexamined. It is shown that the requirements concerning theaerodynamic quality of the body's configuration are not difficult tomeet. V P

A81-17741 ft Variational principles and generalized varia-tional principles for the hybrid aerodynamic problem of airfoilcascades on an arbitrary stream sheet of revolution. G. Liu (ShanghaiInstitute of Mechanical Engineering, Shanghai, Communist China).Sc/entia Sinica, vol. 23, Oct. 1980, p. 1339-1347. 5 refs.

In this paper a hybrid aerodynamic problem of airfoil cascades issuggested and formulated, being a unification as well as a generaliza-tion of the conventional direct and inverse problems, so as to meetvarious requirements of turbomachinery blade design. A newuniversal function - the moment function - is also introduced. Then,two families of variational principles and generalized variationalprinciples are established for the hybrid problem of type A, in whichalong some part of the airfoil contour velocity distribution isprescribed, while along remainder contour geometry is given. Inorder to facilitate the treatment of a variety of boundary conditionsall of them have been converted into natural ones, and use is made ofthe artificial interfaces. This paper is primarily aimed at providing abroader and rigorous theoretical basis for introducing the finiteelement method and other variational methods into computationalaerodynamics of turbomachinery. (Author)

A81-17801 Recent selected papers of Northwestern Poly-technical University. Parts 1 & 2. Xian, Shaanxi, People's Republic ofChina, Northwestern Polytechnical University, 1979. Pt. 1, 203 p.;pt. 2, 243 p. In English and Chinese.

Papers are presented on such topics as the finite differencecomputation of steady transonic potential flow past aircraft, thedesign of subcritical airfoils, the synthesis of array antennas of highdirectivity and low sidelobe, the calculation of the integral-typeflexure hinge assembly of dynamically tuned gyroscopes, thestructural analysis of fuselages with cutouts, and the solidificationcharacteristics of superalloys. Also considered are the matrix analysisof wings, pulsed spray transfer arc welding, color discrimination by acolor-picture reader, the response of a turbojet engine to inletpressure distortion, and the acoustic instability of solid propellantrocket engines. B.J.

A81-17802 ft Finite difference computation of the steadytransonic potential flow around airplanes. S. Luo, Y. Zhen, H. Qian,and D. Wang. In: Recent selected papers of Northwestern Polytechni-

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cal University. Part 1. Xian, Shaanxi, People'sRepublic of China, Northwestern Polytechnical University, 1979, p.1-14. 5 refs. In Chinese, with abstract in English.

The velocity potential equation for steady transonic flow past. an aircraft is solved by mixed finite difference schemes. The finite

difference equations for the velocity potential are solved by the linerelaxation method. The influence of the wing on the horizontal tail iscomputed taking into account the deflection of the wing wakevortices. Two numerical examples are considered and results agreefairly well with wind tunnel test results: (1) a wing-fuselage-horizontal tail-vertical tail configuration at freestream Mach numbersof 0.25 and 0.95; and (2) a wing-fuselage configuration at afreestream Mach number of 1.05 and an angle of attack of 2.2 deg.

B.J.

A81-17803 H Second order approximation theory of anarbitrary aerofoil in incompressible potential flow. C. Lin. In: Recentselected papers of Northwestern Polytechnical University. Part 1.

Xian, Shaanxi, People's Republic of China,Northwestern Polytechnical University, 1979, p. 15-25. 11 refs. InChinese, with abstract in English.

A novel method for calculating incompressible potential flowaround an airfoil is presented. The region outside an arbitary airfoil isconformally transformed into the region outside a unit circle. Thetransformation functions are expanded into ascending power series,and only those terms up to and including the second order areretained. The method gives second-order perturbation solutionswhich are uniformly valid throughout the flow field. Analyticalformulas are given. B.J.

A81-17804 fi Aerodynamic calculations and design of sub-critical aerofoils. C. Lin. In: Recent selected papers of NorthwesternPolytechnical University. Part 1. Xian, Shaanxi,People's Republic of China, Northwestern Polytechnical University,1979, p. 27-35. 20 refs. In Chinese, with abstract in English.

Methods are developed for the analysis of the direct problemand inverse problem of airfoils in subcritical potential flow. Thedirect problem (i.e., the prediction of pressure distribution for agiven airfoil at a given angle of attack) is treated on the basis of acompressibility correction in the second-order approximation theory.It is shown that formulas obtained for the direct problem can becombined with the Newton iteration method to treat the inverseproblem, i.e., the determination of airfoil geometry and angle ofattack for a given pressure distribution. B.J.

A81-17805 " An aerodynamic design method for transonicaxial flow compressor stage. F. Zhu, X. Zhou, S. Liu, and F. Fan. In.Recent selected papers of Northwestern Polytechnical University.Part 1. Xian, Shaanxi, People's Republic ofChina, Northwestern Polytechnical University, 1979, p. 37-49. 9 refs.In Chinese, with abstract in English.

A three-dimensional aerodynamic design method for the tran-sonic axial flow compressor stage is described. The method consistsof three main parts: (1) the mean S2 streamsurface calculation, (2)the approximate calculation of the SI streamsurface of revolution,and (3) the definition of the blade element on the conical surfaceand the stacking of blade airfoil sections. The method is unusual inthat the stations for calculating the S2 streamsurface are curves, andparticularly in that the airfoil parameters of the blade are calculatedon a plane tangent to the approximate streamsurface of revolution.On this tangential plane, two-dimensional flow is used as the basicmodel to calculate the Mach wave system on the suction surface ofthe cascade entrance region. B.J.

A81-17807 H An optimum design procedure of total-temperature thermocouple probes. C. Liu and J. Zhao. In: Recentselected papers of Northwestern Polytechnical University. Part 1.

Xian, Shaanxi, People's Republic of China,Northwestern Polytechnical University, 1979, p. 65-74. 11 refs. InChinese, with abstract in English.

A procedure is described for the design of total-temperaturethermocouple probes for the investigation of turbojet exhaust gas;the aim of the design is to achieve a minimum steady-state errorunder given operating conditions. The gas velocity in the sheath, i.e.,the optimum internal flow velocity, is determined on the principlethat the sum of the radiation error, the conduction error, and thevelocity error is a minimum under give'n operating conditions. Byusing the optimum internal flow velocity, the diameter of theexhaust hole is determined and the layout of the probe is designed.Verification tests have shown that the error of the thermocoupleprobe reaches a minimum when the diameter of the exhaust hole is1.4mm. B.J.

A81-17815 H The automatic matrix force method and tech-niques for handling more complex computations with given comput-er capacity. Q. Yang. In: Recent selected papers of NorthwesternPolytechnical University. Part 1. Xian, Shaanxi,People's Republic of China, Northwestern Polytechnical University,1979, p. 177-188. 10 refs. In Chinese, with abstract in English.

A detailed description is given of the automatic matrix forcemethod, a numerical method of aircraft structural analysis. It isshown that the method can be applied to complex structures with ahigh degree of redundancy. B.J.

A81-17816 H Structural analysis of fuselages with cutoutsby finite element method. S. Ge, C. Sun, X. Tang, and T. Ye. In:Recent selected papers of Northwestern Polytechnical University.Part 1. Xian, Shaanxi, People's Republic ofChina, Northwestern Polytechnical University, 1979, p. 189-200. 6refs. In Chinese, with abstract in English.

A finite element procedure is developed for the structuralanalysis of fuselages with cutouts. It is shown that, when the elasticbehavior of the bulkhead is considered, the normal stresses exhibit athree-wave circumferential variation. Calculated displacements alongthe length of the fuselage are in agreement with full-scale test data.

B.J.

A81-17818 H The matrix analysis of wings. Y. Xu, R. Zhu,J. Jiang, and Y. Cai. In: Recent selected papers of NorthwesternPolytechnical University. Part 2. Xian, Shaanxi,People's Republic of China, Northwestern Polytechnical University,1979, p. 41-62. In Chinese, with abstract in English.

A matrix analysis is presented in which plate-beam wingstructures are simplified either as plane stress or plate bendingmodels. In addition to applying the element stiffness matrix of planestress, the paper introduces a triangular element matrix for laminatedplates and an element stiffness matrix for beams of axially variablerectangular cross section. Two general computer programs arepresented, and numerical results are given for the deflections andstresses of a wing consisting of plates and beams, a honeycomb-corewing, and a solid wing. B.J.

A81-17824 j A preliminary experimental investigation ofthe response of a turbojet engine to inlet pressure distortion. F.Chen, D. Tang, Z. Hu, W. Li, J. Yu, X. Wu, J. Zhao, Q. Lin, Z. Wang,and S. Liu. In: Recent selected papers of Northwestern PolytechnicalUniversity. Part 2. Xian, Shaanxi, People'sRepublic of China, Northwestern Polytechnical University, 1979, p.169-185. 8 refs. In Chinese, with abstract in English.

Preliminary results are presented concerning the influence ofinlet pressure distortion on the characteristics and instability of theaxial compressor of a turbojet engine. Experiments were performedon the test bed of a turbojet engine with a 9-stage compressor whosefirst stage is transonic. It is found that the inlet pressure distortionaffects not only the stall line but also the shape and position ofconstant speed lines of the compressor. Inlet pressure distortionshifts the speed lines toward the left and flattens them. The effect ofthe decrease in the first stage nozzle exit area is similar to that ofinlet pressure distortion. B.J.

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A81-17825 H The measurement and analysis of stationparameters of a turbojet engine. Q. Dong, J. Zhao, S. Liu, X. Wu, Z.Hu, M. Cong, Q. Lin, Z. Wang, S. You, and L. Zheng. In: Recentselected papers of Northwestern Polytechnical University. Part 2.

Xian, Shaanxi, People's Republic of China,Northwestern Polytechnical University, 1979, p. 187-201. 11 refs. InChinese, with abstract in English.

The flow field parameters at characteristic stations of a turbojetengine were measured under design operating conditions. These datawere used to calculate the gasdynamic parameters of the characteris-tic stations, the main process parameters, the component losscoefficients, and the engine performance. The parameters of theengine under various throttle conditions were recorded for differentspeeds, different nozzle areas, and with and without compressorbleeding. Attention is also given to the rational selection of probelocations to take due consideration of flow field characteristics, andto the selection of the proper method of data processing forobtaining accurate average station parameters of the engine. B.J.

A81-17826 S! An experimental investigation of the rotatingstall, surge, and wake behind the rotor for a single stage axialcompressor. W. Zhang, Z. Liu, C. Zhang, and J. Liu. In: Recentselected papers of Northwestern Polytechnical University. Part 2.

Xian, Shaanxi, People's Republic of China,Northwestern Polytechnical University, 1979, p. 203-215. 8 refs. InChinese, with abstract in English.

Dynamic measurements were used to study the rotor, rotatingstall, and surge of a single-stage axial compressor (design speed of15,000 rpm). The rotating stall is found to be related to the totalturbulence caused by the wake of the rotor. It is shown that beforerotating stall occurs, the wake range of the rotor widens, the shape ofthe wake changes significantly, and the total turbulence caused bythe wake increases sharply. It is also shown that surge occurs as aresult of continuous expansion of the rotating stall cell. As soon assurge occurs, distinct reverse flow appears; the flow pulse frequencyof surge is far less than that of rotating stall. B.J.

A81-17827 It A vaporizing combustor with double combus-tion spaces. M. Tang, H. Zhu, and Q. Du. In: Recent selected papersof Northwestern Polytechnical University. Part 2.

Xian, Shaanxi, People's Republic of China, NorthwesternPolytechnical University, 1979, p. 217-228. 5 refs. In Chinese, withabstract in English.

A tubular combustor is described that has a novel type ofprevaporizing tube, which is of annular cross section. The dome ofthe combustor is divided into two combustion spaces; fuel is injectedunder moderate pressure into the annular space of the prevaporizingtube through the orifices on the two fueled-distribution rings. Theinjected fuel forms oil films on the two walls. The combustor isdesigned to be used as an air heater for a high-temperature windtunnel. It is required that the combustor provide a steady uniformhot gas stream at a temperature of 400-1100 C, and that the flamenot extend beyond the exit of the flame tube. B.J.

A81-17832 Sukhoi's pivotal interdictor. Air International,vol. 20, Jan. 1981, p. 6-10.

The article covers the development, design, and operation of theSoviet Su-24 aircraft, NATO code name 'Fencer'. The Su-24 isconfigurationally similar to its USAF counterpart, the F-111,although scaled down both dimensionally and in weight (emptyequipped weight of 41,890 Ib rising to a maximum weight of 87,080Ib). It has a combat radius of 1700 km and can attain speeds of 2445km/hr (M = 2.3) above 36,000 ft and 1470 km/hr (M = 1.2) at sealevel. The aircraft is powered by a pair of Tumansky R-29Bturbofans (42% more unreheated thrust than the TF30-P-9 of theF-111), with five LP and six HP compressor stages and a maximumunreheated thrust of 17,636 Ib. The Su-24 is equipped with a radarof the pulse-Doppler type for navigation, terrain-following, andall-weather weapons delivery, and its armament is comprised of a

23-mm Gatling-style rotary cannon and nine weapons stationscontaining a total of 16 1,102-lb bombs. The Su-24 is capable ofinterdiction missions far beyond the PLOT (Front Line of Troops)and is most effective in a HI-LO-HI profile from its Soviet bases.Fencer is being delivered at a production rate of 8-9 monthly, andrepresents an important advance in Soviet attack capability. B.R.K.

A81-17841 # An experimental study on kerosene-hydrogenhybrid combustion in a gas turbine combustor. H. Hiroyasu, M. Arai,T. Kadota (Hiroshima, University, Hiroshima, Japan), and J. Yoso(Japanese National Railways, Tokyo, Japan). JSME, Bulletin, vol. 23,Oct. 1980, p. 1655-1662. 7 refs.

Kerosene-hydrogen hybrid combustion was studied in a swirlertype combustor. Kerosene was atomized by an air blast atomizer,and gaseous hydrogen was supplied to a kerosene spray through anannular slit in the atomizer. Blow out limit of the flame shifts to thelean side of the air-fuel mixture in the hybrid combustion, whichresults in a slight decrease in NOx emission and a decrease in sootemission. When the hybrid ratio is under 10%, the flame stability isimproved by hybrid combustion; increasing the hybrid ratio from 10to 50% produces an increased combustion efficiency and reductionsof soot and NOx. (Author)

A81-17952* # Inlet flow distortion in turbomachinery. B. S.Seidel, M. D. Matwey (Delaware, University, Newark, Del.), and J. J.Adamczyk (NASA, Lewis Research Center, Cleveland, Ohio). Ameri-can Society of Mechanical Engineers, Gas Turbine Conference andProducts Show, New Orleans, La., Mar. 10-13, 1980, Paper80-GT-20. 6 p. 12 refs. Members,.$1.50; nonmembers, $3.00. GrantNo. NsG-3189.

A single stage axial compressor with distorted inflow is studied.The inflow distortion occurs far upstream and may be a distortion instagnation temperature, stagnation pressure or both. The blade rowsare modeled as semi-actuator disks. Losses, quasi-steady deviationangles, and reference incidence correlations are included in theanalysis. Both subsonic and transonic relative Mach numbers areconsidered. A parameter study is made to determine the influence ofsuch variables as Mach number and swirl angle on the attenuation ofthe distortion. (Author)

A81-17953 * # Comparison of experimental and computation-al shock structure in a transonic compressor rotor. G. Haymann-Haber (General Electric Corp., Lyman, Mass.) and W. T. Thompkins,Jr. (MIT, Cambridge, Mass.). American Society of MechanicalEngineers, Gas Turbine Conference and Products Show, NewOrleans, La., Mar. 10-13, 1980, Paper 80-GT-81. 11 p. 17 refs.Members, $1.50; nonmembers, $3.00. Grant No. NGL-22-009-383.

Measurement of passage shock strength in a transonic compres-sor rotor using a gas fluorescent technique revealed an unexpectedvariation in shock strength in the radial direction. An axisymmetricidealization would normally predict that the passage shock strengthwould gradually weaken when moving radially inward until disap-pearing at the sonic radius. However, the measurements indicated asharp peak in strength at the nominal sonic radius. Blade boundarylayer separation originating at this point accounts for about one halfof the total rotor losses. A numerical computation of the three-dimensional inviscid flow, using time-marching techniques, hasaccurately predicted in general the radial and tangential variations inpassage shock strength and in particular the sharp pressure peak atthe nominal sonic radius. The overall shock strength was somewhatoverpredicted, but this overprediction may be the result of boundarylayer separation in the experiment. This paper presents comparisonsbetween the optical density measurements and computational resultsand in addition a short analytical discussion which demonstrates thatthe sharp shock strength rise may occur in many transoniccompressor rotors. • (Author)

A81-17954 * H Structure and decay characteristics of tur-bulence in the near- and far-wake of a moderately loaded compressor

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rotor-blade. A. Ravindranath and B. Lakshminarayana (PennsylvaniaState University, University Park, Pa.). American Society of Mechani-cal Engineers, Gas Turbine Conference and Products Show, NewOrleans, La., Mar. 10-13, 1980, Paper 80-GT-95. 10 p. 9 refs.Members, S1.50; nonmembers, S3.00. Grant No. NsG-3012.

The wake of a turbomachinery rotor-blade is turbulent, highlythree-dimensional, and nonisotropic with appreciable curvature inthe trailing-edge and near-wake regions. The characteristics of theturbulence vary considerably with radius, blade loading, free-streamturbulence, Reynolds number, and the rotor-blade geometry. Thispaper is concerned with the turbulence properties of a moderatelyloaded compressor blade, particularly near the blade trailing-edge.The tangential variation of the axial, tangential and radial intensitiesand stresses across the wake, as well as their decay characteristicswere measured with a tri-axial hot-wire probe in the rotor frame ofreference. The decay of intensities and stresses were found to be veryrapid in the trailing-edge and near-wake regions and slow in thefar-wake region. The effects of inlet-guide-vane and the hub-wallboundary layers on the rotor wake turbulence spectra are alsodiscussed. Similarity rules for the three components of intensity arealso derived and presented in this paper. (Author)

A81-17976 History of flight testing the L-1011 Tristar jettransport. I - The L-1011-1. R. J. Gatineau (Lockheed-California Co.,Engineering Flight Test Div., Palmdale, Calif.). Lockheed Horizons,Winter 1980-1981, p. 3-17.

The article highlights the flight testing and development of theL-1011 Tristar jet transport. The L-1011 has a take-off gross weightof 430,000 to 504,000 Ib, a range of up to 5000 nautical miles, andcan carry 300 to 345 passengers at a nominal cruise speed of Mach0.83. The L-1011 is currently available in four basic models(L-1011-1, L-1011-100, L-1011-200, L-1011-500), each model hav-ing differences in design, range, fuel capacity, and passenger capacity.The aircraft were intensively tested overa a period of two years fortake-off and landing, noise levels, load capacity, strucural defects,aircraft system and and component performance, and flight perfor-mance in a series of tests designed to meet the flight demonstrationrequirements necessary for certification, which was received from theFAAin1972. B.R.K.

A81-17977 Autonomous navigation using passively sensedterrain images. O. Firschein and M. J. Hannah (Lockheed SignalProcessing Laboratory, Palo Alto, Calif.). Lockheed Horizons, Winter1980-1981, p. 26-34.

The possibility of using passively sensed terrain images as thebasis for an autonomous navigation system in subsonic vehicles flyingat low altitudes is of interest for unmanned flight applications.Through a TV camera or mosaic of light-sensitive semiconductordevices, the image scene is converted into a number which is storedin a computer and can then be used by the 'Navigation Expert' (acomputer program being developed at Lockheed's Signal ProcessingLaboratory) to make decisions and control the vehicle's flight. TheNavigation Expert coordinates several subsystems including theInstruments Subsystem (IS), a Dead Reckoning System (DRS), aGround Velocity Subsystem (GVS), a Visual Bootstrapping Sub-system (VBS), and a Landmarks Subsystem (LS). Further research isnecessary before an automatic navigation system based on images canbecome operational. B.R.K.

A81-17994 Influence of free-stream turbulence intensityon heat transfer in the two-dimensional turbulent boundary layer ofan accelerated compressible flow. K. Bauer, J. Straub, and U. Grigull(Miinchen, Technische Universitat, Munich, West Germany). Interna-tional Journal of Heat and Mass Transfer, vol. 23, Dec. 1980, p.1635-1642. 10 refs. Research sponsored by the Bundesministeriumder Verteidigung.

The effect of free-stream turbulence on heat transfer in theturbulent boundary layer is investigated experimentally for accelerat-ed compressible flow in a two-dimensional convergent-divergentnozzle. The turbulence intensity varied from nearly zero to about

20%; and the nozzle entrance Reynolds number attained a value ofabout 10-million. For three different loading cases the free-streamturbulence intensity and fluctuation along the nozzle axial length aredetermined together with the local Stanton number. For lowReynolds number (less than one-million) no clear change of heattransfer is observed; for Re exceeding one-million, a weak and nearlylinear dependence of Stanton number on free-stream turbulenceintensity is shown. B.J.

A81-17997 Vector and scalar characteristics of opposingjets discharging normally into a cross-stream. Z. A. Khan and J. H.Whitelaw (Imperial College of Science and Technology, London,England). International Journal of Heat and Mass Transfer, vol. 23,Dec. 1980, p. 1673-1680. 10 refs. Research supported by the ScienceResearch Council.

Measurements of mean velocity and a passive scalar (heliumtracer) have been obtained for two rows of opposing jets dischargingnormally into a cross-flowing stream and simulate an importantaspect of gas-turbine combustor practice. Results are presented for adownstream distance of 6 jet diameters from the jet center lines andfor a jet-to-mainstream velocity ratio of 2.25. The influence of thenonuniform pitch and pitch-to-diameter ratio is quantified with theopposing jets separated by 4D. For a pitch to diameter ratio of 2, aslight geometrical asymmetry of the central jet for one row of holesresults in a severe asymmetry of the velocity field. This effect is not,however, propagated to the opposing side. The scalar flux measure-ments show the nearest adjacent jet aiding the displaced jet to regainsymmetry and the counteraction to this of the opposing jet. With apitch-to-diameter ratio of 4, the scalar measurements indicate'slipping' between the opposed jets. Furthermore, symmetricalarrangement of the jets with this higher pitch-to-diameter ratio leadsto impingement of the opposing jets with the jets bifurcatingasymmetrically, and geometrical asymmetry no longer results insevere asymmetry of the velocity field. (Author)

A81-18022 # Effects of axisymmetric sonic nozzle geometryon Mach disk characteristics. A. L. Addy (Illinois, University,Urbana, III.). AIAA Journal, vol. 19, Jan. 1981, p. 121, 122. 13 refs.

Results are presented on the effects of axisymmetric sonicnozzle geometry on the onset, diameter, and location of the Machdisk in moderately underexpanded freejet flows. A contouredconverging nozzle, four conically converging sharp-edged nozzles anda sharp-edged orifice are examined. The mass flow rate and chokingcharacteristics of the six sonic nozzles are investigated over thestagnation to back pressure ratio range greater than 1 and less than10. R.C.

A81-18024 # A study of multiple jets. S. Raghunathan andI. M. Reid (Belfast, Queen's University, Belfast, Northern Ireland).AIAA Journal, vol. 19, Jan. 1981, p. 124-127.

This paper investigates the reduction of noise level through amultiple jet array. Nozzles are equally spaced around a circle with aradius of 5 mm from the axis of the central nozzle, and operate at asupply pressure of 0.3-0.5 MPa (3-5 bar). A noise spectra peakcorresponding to f = 20 KHz is found. Noise reduction is observedwithout significant reduction in the momentum of the jet. R.C.

A81 18051 International Air Transportation Conference,New Orleans, La., April 30-May 3, 1979, Proceedings. Volumes 1 &2. Conference sponsored by ASCE, SAE, AIAA, ICE, ATRIF, andTransportation Research Board. New York, American Society ofCivil Engineers, 1979. Vol. 1, 485 p.; vol. 2, 343 p. Price of twovolumes, $59.

The conference included papers on airspace analysis in airportsystem planning, performance of flexible highway pavements, micro-wave landing systems, civic-electrical engineering interface, hedgingagainst errors in airport forecasting, a computer program for slabswith discontinuities, and flight instrumentation for all-weatherapproach and landing. Also discussed were air service for smallcommunities, helicopters for all-weather terminals, NOT techniques,

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airline deregulation, runway configuration management systems, andthe role of aircraft separation assurance in the cockpit. A.T.

A81-18052 Airspace analysis in airport system planning.G. W. Antis, W. J. Dunlay, Jr., H. Fan (Peat, (Warwick, Mitchell andCo., San Francisco, Calif.), and C. Brittle (Metropolitan Transpor-tation Commission, Berkeley, Calif.). In: International Air Trans-portation Conference, New Orleans, La., April 30-May 3, 1979,Proceedings. Volume 1. New York, AmericanSociety of Civil Engineers, 1979, p. 1-15.

An airspace capacity model was used to estimate the capacity ofthe San Francisco Bay Area airspace under a variety of differentoperating conditions. The results were compared with alternativeforecasts of aviation demand in 1997. The comparisons of demandwith airspace capacity led to conclusions on: (1) the extent to whichthe Bay Area airspace will be able to accommodate future aviationactivity, and (2) the locations of critical capacity constraints andairspace interactions. T.M.

A81-18054 Introduction to a rigid pavement design proce-dure. W. R. Barker (U.S. Army, Geotechnical Laboratory, Vicksburg,Miss.). In: International Air Transportation Conference, New Or-leans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers, 1979,p. 33-48. 16refs.

Description of a new mechanistic procedure for the structuraldesign of rigid airport pavements to carry the design traffic underfield conditions. The technique involves three major elements: (1)material characterization, (2) computation of load response param-eters, and (3) correlation of the load response parameters topavement performance. One limitation of the procedure is that itmust be restricted to standard jointed Portland cement concretepavements. T.M.

A81 -18055 Micro-wave landing system - An operationalpoint of view. A. J. Beatty (International Federation of Air LinePilots Association, Egham, Surrey, England). In: International AirTransportation Conference, New Orleans, La., April 30-May 3, 1979,Proceedings. Volume 1. New York, AmericanSociety of Civil Engineers, 1979, p. 49-53.

The official position of the International Federation of Air LinePilots Association (IFALPA) is given regarding the need for a newnonvisual approach and landing guidance system. The argument ismade that early implementation of the micro-wave landing system(MLS) will enhance the safety, reliability and economy of interna-tional civil air operations. The paper does not attempt to investigatein detail the mechanisms of MLS and the theory of its signalpropagation. It does, however, investigate its use by the line pilotfrom the operational point of view, including its effect on commer-cial air transport. (Author)

A81-18056 RNAV benefits today - Today and futurerequirements. R. A. Berube (National Airlines, Inc., Clifton, N.J.).In: International Air Transportation Conference, New Orleans, La.,April 30-May 3, 1979, Proceedings. Volume 1.New York, American Society of Civil Engineers, 1979, p. 54-71. 37refs.

Presently experienced and expected future benefits of areanavigation systems are reviewed as they relate to the economy,safety, and workload of flight operations. Minimum system charac-teristics and functional requirements are tabulated on the basis ofpersonal experience, simulations, tests, and postulated aspects of theRNAV environment. T.M.

The rationale, operations, and expected benefits are describedfor the implementation of fifty passenger DeHavilland Dash-7aircraft in the Alleghany commuter fleet of Ransome Airlines. Theinovative use of STOL aircraft, 30 RNAV, and stub ends of runwaysis argued to have large potential effects on intercity air transporta-tion. T.M.

A81-18058 Testing model rotorcraft for overwater opera-tions. W. A. Crago and D. L. Williams (British Hovercraft Corp., Ltd.,Experimental and Electronic Laboratories, East Cowes, Isle of Wight,England). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers,1979, p. 137-152.

This paper presents a brief historical review of some of theproblems associated with the ditching and flotation of helicopters. Italso discusses the sea conditions likely to be met and shows how thevarious phenomena involved can be investigated by means of modelexperiments. (Author)

A81-18059 Flight instrumentation requirements for all-weather approach and landing. J. L. DeCelles and G. Terhune (AirLine Pilots Association, Kansas City, Mo.). In: International AirTransportation Conference, New Orleans, La., April 30-May 3, 1979,Proceedings. Volume 1. New York, AmericanSociety of Civil Engineers, 1979, p. 153-164. 5 refs.

The official position and rationale of the Air Line PilotsAssociation (ALPA) is given regarding instrumentation requirementsfor air carrier approach and landing. The argument is made that thecost of continuing the status quo is greater (in terms of safety,reliability and economy) than the expense of providing the necessaryimprovements. The paper expounds the inadequacy of conventionalinstrumentation for operating to present and future visibilityminima, and it presents the rationale for ALPA's contention thatthese inadequacies can be overcome only by head-up display (HUD)of suitable information to the pilot. (Author)

A81-18060 New major U.S. airports - Capacity considera-tions. V. J. Drago (Battelle Columbus Laboratories, Columbus,Ohio). In: International Air Transportation Conference, New Or-leans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers, 1979,p. 165-178. 9 refs.

A methodology is developed to investigate the need for majornew airports at 21 U.S. hubs through the year 2000. Thismethodology is based on calculating average runway delays forvarious airport activity and operational scenarios. Cost estimates aregiven for the required new facilities. (Author)

A81-18061 An overview - 1980 generation avionic devel-opments. T. A. Ellison (United Air Lines, Inc., Chicago, III.). In:International Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 1. .NewYork, American Society of Civil Engineers, 1979, p. 179-186.

The 1980 generation air transports now under development willincorporate a completely new generation of avionics devices andinterfaces, briefly described. The major changes in 1980 avionics willbring new benefits and new problems to the operator. Integration ofinformation through improved computation and display facilities willbetter optimize aircraft operation. Some of the benefits can beforecast from data recorded in current aircraft operations. Means aresuggested to utilize and maintain new avionics capabilities effectivelyin the transition environment of the 1980's. (Author)

A81-18057 The introduction of STOL and RNAV to largecommercial operations. C. J. Blaydon (Ransome Airlines, Bensalem,Pa.). In: International Air Transportation Conference, New Orleans,La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers, 1979, p. 85-94.

A81 -18062 Non-destructive pavement evaluation. M. E.Harr (Purdue University, Lafayette, Ind.). In: International AirTransportation Conference, New Orleans, La., April 30-May 3, 1979,Proceedings. Volume 1. New York, AmericanSociety of Civil Engineers, 1979, p. 213-219. 9 refs.

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A81-18063 Prestressed concrete airfield pavements. R.Heinen (Dyckerhoff and Widmann, Inc.; Dywidag Canada, Ltd.,Canada). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers,1979, p. 220-235.

A81-18064 Automating airborne company communica-tions. R. E. Johnson (United Air Lines, Inc., San Francisco, Calif.).In: International Air Transportation Conference, New Orleans, La.,April 30-May 3, 1979, Proceedings. Volume 1.New York, American Society of Civil Engineers, 1979, p. 236-242.

As industry matures, the authority to accomplish changeswithout financial controls is reduced. This paper will outline how theAir Transport Industry finally launched a major change in communi-cations with their aircraft after years of development. In order tomeet financial goals, the scope of the programs were reduced andtechnology advances were utilized to provide answers not previouslyavailable. (Author)

A81-18065 Helicopters - Help for the all weather terminal.J. C. Kettles (Petroleum Helicopters, Inc., Lafayette, La.). In:Internationa! Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 1. NewYork, American Society of Civil Engineers, 1979, p. 243-247.

A81 -18066 Runway rehabilitation, Washington NationalAirport. F. Moavenzadeh and M. J. Markow (MIT, Cambridge,Mass.). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers,1979, p. 249-264.

The structural condition of a runway flexible pavement atWashington National Airport was evaluated. Since its last overlay in1972, the runway has exhibited horizontal and vertical permanentdeformations or distortions, including lateral distortions of surfacepaint and groove patterns, vertical heaves and troughs, and localizeddepressions. Pavement and soils investigations carried out to identifythe causes of these distress mechanisms indicated that observedpavement damage was related more to materials properties andperhaps construction practices, rather than to structural adequacy.Recommendations included: (1) removal of severely distressedmaterial, either by cold-planing or other means; (2) replacement ofdamaged material with a stiff, high-tensile-strength asphalt concretebase; and (3) overlay of entire pavement surface with an epoxyasphalt layer to resist horizontal stresses induced by braking andturning aircraft and to retard cracking. (Author)

A81-18067 Community participation in airport planning.B. D. Myers (Missouri, Aviation Dept., Kansas City, Mo.). In:International Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 1. NewYork. American Society of Civil Engineers, 1979, p. 265-274.

Several principles and techniques for community and citizenparticipation were exercised during the Kansas City InternationalAirport Master Plan and Environs Area Plan update. These proce-dures include establishing advisory and policy committees, a projectinformation center, the conducting of public information meetings,and various other methods of providing information on the plan forthe publics consideration. Advice from the community assisted inshaping the final airport and environs plan. The public must berepresented in the continuous planning process. (Author)

A81-18068 Aviation assumptions in the eighties. D. E.Raphael (Transportation Research Board, Washington, D.C.; SRIInternational, Menlo Park, Calif.). In: International Air Transporta-tion Conference, New Orleans, La., April 30-May 3, 1979, Proceed-ings. Volume 1. New York, American Society ofCivil Engineers, 1979, p. 276-282.

Respondents to a comprehensive survey concerning the aviationindustry are generally optimistic but watchful about the prospectsfor the growth in the 1980s. Identifying factors most likely toinfluence air transportation demand was a major purpose of theOctober 1978 survey of 120 forecasters, planners, and researchers,who came from four different global -regions and six differentindustry sectors. The survey results presented in this paper showchanges in real air fares and real economic growth to be therespondent's chief bellwethers, followed closely by jet fuel availabil-ity and price, and government regulation. Also considered in thesurvey are modifiers that would be most disruptive to the industry;here, a prolonged OPEC embargo, a major recession, and furtherlarge cuts in air fare discounts topped the list. Base-line values forcertain assumptions are also provided. Comparisons are made amongrespondents in different regions and industry sectors. (Author)

A81-18069 A new perspective in aviation systems plan-ning. M. J. Ryan, Jr. (Metropolitan Council of the Twin Cities, St.Paul, Minn.). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers,1979, p. 283-291.

New and increased emphasis on maximizing the use of existingaviation facilities, particularly in large urban areas, has placedconsiderably more responsibility on the metropolitan aviation systemplanners. As part of the process of maintaining a system planresponsive to the area's air transportation needs, the systems planneris the key to protecting and preserving the continued viability of themetropolitan areas' airport system, including both air carrier andgeneral aviation airports. Given that few, if any, new air carrierairports will be built prior to the end of the century, the aviationsystem planners' role must be centered on coordinating airport planswith community comprehensive plans. This is especially true withrespect to the airport/land use compatibility planning currentlyunderway at some airports around the nation, including the TwinCities. (Author)

A81-18070 * Avionics and displays in a future airspacesystem. S. Salmirs (NASA, Langley Research Center, Hampton, Va.).In: International Air Transportation Conference, New Orleans, La.,April 30-May 3, 1979, Proceedings. Volume 1.New York, American Society of Civil Engineers, 1979, p. 292-309.10 refs.

The terminal configured vehicle (TCV) program was conceivedto address the problems of (1) operation in the crowded terminalarea airspace, and (2) integration of airborne avionics systemsnecessary to improve the efficiency of these operations. The programand its interaction with industry task groups are summarized,including elements of research and data collection. New technologyis discussed which may be useful in implementing some definedavionics and display requirements. T.M.

A81-18071 The problems of helicopter ditching. J. Scan-Ion (Civil Aviation Authority, London, England). In: InternationalAir Transportation Conference, New Orleans, La., April 30-May 3,1979, Proceedings. Volume 1. New York, Ameri-can Society of Civil Engineers, 1979, p. 310-324.

Technical reasons for the occurrence of emergency helicopterditchings are reviewed in an attempt to survey current approaches tothis problem. Existing legislation affecting overwater operations andairworthiness is examined, and problems of survivability are consid-ered, ranging from evacuation of the helicopter to the search andrescue facilities. T.M.

A81 -18072 Canada's national aviation forecasting models.W. T. Tucker (Canadian Air Transportation Administration, Ottawa,Canada). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 1.

New York, American Society of Civil Engineers,1979, p. 343-357.

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This paper outlines the role of the Canadian Department ofTransport in airport planning and site-specific forecasting. It thenprovides an overview of the national system of aviation forecastingmodels currently being developed and describes the progress to date.Two of these models, viz., the Air Passenger Origin and DestinationModel (PODM) and the Passenger Traffic Allocation Model (PTAM),were recently completed and these are described in some detail.Finally, a brief summary is given of other forecasting methods andmodels with specific reference to planning peak period forecasts.

(Author)

A81-18073 The federal role in airport noise controlplanning. J. E. Wesler (FAA, Washington, D.C.). In: International AirTransportation Conference, New Orleans, La., April 30-May 3, 1979,Proceedings. Volume 1. New York, AmericanSociety of Civil Engineers, 1979, p. 375-382.

Since receiving statutory authority in 1968, the FAA hasdeveloped and followed a step-by-step, deliberate program to imposenoise limits on all aircraft. Noise reduction at the source cannot solvethe aviation noise problem, however, since aircraft can never besilent. Recognizing this, the Department of Transportation(DOTI/FAA Aviation Noise Abatement Policy of November 18,1976, spells out the shared responsibilities among all elements of theaviation community for aviation noise abatement. This paper reviewsbriefly these shared responsibilities for aviation noise abatement, anddescribes those functions which the Federal government is fulfilling.

(Author)

A81-18074 L-1011 Flight Management System designconsiderations. F. F. Wright and R. J. Oliver (Lockheed-CaliforniaCo., Burbank, Calif.). In: International Air Transportation Con-ference, New Orleans, La., April 30-May 3, 1979, Proceedings.Volume 1. New York, American Society of CivilEngineers, 1979, p. 383-398.

This paper describes some of the design considerations related to

the fuel and cost savings aspects of the L-1011 Flight ManagementSystem. Reductions in fuel and cost are achieved by optimizing thethrust and speed in the climb, cruise and descent regimes of flight.The system mechanization, operation and design problems toaccomplish this optimization are discussed. (Author)

A81-18075 Fully bonded concrete overlay for an airportrunway. E. J. Barenberg (Illinois, University, Urbana, III.) and B. L.Ratterree (Crawford, Murphy and Tilly, Inc., Springfield, III.). In:International Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 1. NewYork, American Society of Civil Engineers, 1979, p. 399-416. 6 refs.

Fully bonded concrete overlays are a viable method forrehabilitating concrete pavements. Use of this procedure for upgrad-ing concrete pavements has been limited by the expensive andenvironmenatlly objectional procedure of acid etching the existingpavement surface. With the newly developed machinery capable ofmilling off a thin layer of the existing concrete, acid etching of thesurface is no longer required, making this approach more economical-ly and environmentally attractive. This paper describes the designanalyses leading to the selection of a fully bonded concrete overlayto rehabilitate and upgrade an existing concrete runway, and theconstruction procedures used to assure full bonding of the overlay tothe pavement. (Author)

A81-18076 UK pavement design and evaluation - A newapproach. R. M. Hutson (Department of the Environment, Direc-torate of Civil Engineering Services, Croydon, Surrey, England). In:International Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 1. NewYork, American Society of Civil Engineers, 1979, p. 417-426. 8 refs.

The features of an aircraft pavement classification system arereviewed and a new approach to matching aircraft and pavements isoutlined. The system is based on the use of reference constructionmaterials with defined mechanical properties representative of rigid

and flexible pavement construction. The depth of constructionrequired by individual aircraft using their unique landing gearconfigurations is established over a range of subgrade support valuesfrom weak to strong. Pavements are classified by establishing therelationship between actual construction on their assessed subgradesupport value to an equivalent depth of reference construction bythe use of equivalency factors. The problem of limited weight andoverload aircraft operations are considered. (Author)

A81 -18077 Omega - An economic Loran A replacement.L. L. James (Trans World Airlines, Inc., Kansas City, Mo.). In:International Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 1. NewYork, American Society of Civil Engineers, 1979, p. 439-452. 7 refs.

A81-18078 Recent developments in NOT techniques. G.T. Baird and J. P. Nielsen (New Mexico, University, Albuquerque, N.Mex.). In: International Air Transportation Conference, New Or-leans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers, 1979,p. 481-493.

The Civil Engineering Research Facility developed three non-destructive pavement testing methods starting with Thumper I whichused a steady-state vibrator to determine the wave propagationproperties of the pavement. This system's shortcomings included anon-air-transportable van and complex electronics requiring highlytrained personnel. The Thumper II excluded these problems byutilizing a drop weight impact source and basic recording equipment,but needed a computer center to digitize and process the recordedsignals. The Thumper III is the most modern system which combinesair-transportability with the on-board minicomputer resulting inquick and reliable airfield testing. A.T.

A81-18079 Investment decision-making in internationalairports. P. H. Beinhaker (IBI Group, Toronto; Beinhaker/lrwinAssociates; InterBase, Inc.; Beinhaker Planning and DevelopmentServices, Ltd., Canada). In: International Air Transportation Confer-ence, New Orleans, La., April 30-May 3, 1979, Proceedings. Volume2. New York, American Society of Civil Engi-neers, 1979, p. 494-503.

The paper discusses the maximization of the initial land resourcefor airport facilities and the insurance of the protection of airportland and investments by insuring compatible land development onadjacent lands. The location of airport facilities in the closeproximity of the airfield with adequate provisions for the expansionof passenger and ground access facilities is discussed. The maximumproductivity in land use can be provided by charging land rents inaccordance with the accessibility to the airfield; environmentalfactors should be accounted for by relating the costs of mitigation tothe operations and/or facilities causing the problem and recoveringthe costs through charges. A.T.

A81-18080 Increasing capacity with computer-assisted de-cision making. R. G. Dear (California State University, Fullerton,Calif.). In: International Air Transportation Conference, New Or-leans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers, 1979,p. 519-538.

Computer use in the high density terminal areas is discussedwith the aim of increasing airport capacity, decreasing delays, andaiding sequencing and scheduling performed by controllers. Amethod of Constrained Position Shifting (CPS) was developed whichis based on resequencing on the first-come, first-serve order withrespect to arrival on the runway; simulation is presented for onesimple CPS strategy which limits each aircraft to a maximum shift offour positions from its first position (forward or rearward). It wasshown that significant improvements in system performance can beattained along with potential savings. A.T.

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A81-18081 Helicopter survivability in overwater situa-tions. M. J. Evans (British Airways Helicopters, Ltd., Aberdeen,Scotland). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers,1979, p. 539-552,

A81 -18082 Computer generated displays and pilot effec-tiveness. D. M. Fadden and E. F. Weener (Boeing CommercialAirplane Co., Seattle, Wash.). In: International Air TransportationConference, New Orleans, La., April 30-May 3, 1979, Proceedings.Volume 2. New^York, American Society of CivilEngineers, 1979, p. 553-561.

On-board digital computers and electronic display equipmentfor 757 and 767 aircraft permit almost any reasonable format orpresentation and computation of flight parameters previously un-available for display. Previous computer display programs haveindicated the necessity of dynamic simulation to maximize displayeffectiveness; optimization in the format of information displays canreduce the mental calculations by the pilot, allowing more time formanaging the flight. The pilot panel mockup, pilot adaptationenhancement, and the duties of the pilot as the flight manager areoutlined, concluding that the new computer displays will allow thepilot to operate more accurately and efficiently. AT.

A81 -18083 Airport visual approach, guidance and landingsystems - Airline pilots viewpoint. J. A. Forgas (Air Line PilotsAssociation, Washington, D.C.). In: International Air TransportationConference, New Orleans, La., April 30-May 3, 1979, Proceedings.Volume 2. New York, American Society of CivilEngineers, 1979, p. 562-567.

A81-18084 Design of the new Tehran International Air-port. R. J. Hodge (Tippetts-Abbett-McCarthy-Stratton, Washington,D.C.). In: International Air Transportation Conference, New Orleans,La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers, 1979,p. 572-585.

This paper covers the design concepts, considerations andparameters for a new major international airport in the Middle East.Included are discussions on the airfield, the terminal complex, aircargo facilities, aircraft support facilities and airport service facilities.

(Author)

A81 -18085 Modeling of the terminal area Air TrafficManagement and Control. C.-C. Hsin (Mitre Corp., Metrek Div.,McLean, Va.). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers,1979, p. 586-605. 5 refs.

A study of the advanced terminal area Air Traffic Managementand Control (ATM/C) system included the basic structures andcontrol elements, and the design of advanced automation methods. Itwas shown that the terminal area ATM/C is stochastic and can beeffectively measured; the problem is complex due to numeroussubsystems and various control functions. Both the generation andthe transmission of information should be emphasized to improvethe ATM/C; continuous improvements of the surveillance, communi-cation and tracking capabilities are required to accomodate theadvanced automation functions. A.T.

A81-18086 Airspace simulation in airport system plan-ning. E. S. Joline (Aviation Simulations International, Inc., Hunting-ton, N.Y.). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers,1979, p. 606-617.

The ASM-3 airport simulation model has been designed for easyadaptation to various applications to maintain analysis costs in

balance with other components of the airport planning program. TheASM-3 system includes a highly modular structure so that individualroutines, such as runway assignment rules, can be easily recorded andreplaced without changing the balance of the program; the spacesimulation model is comprised of a number of computer algorithmswhich approximate the flight planning and plan-executing functionsof the pilot and air traffic controller. An example of airspacesimulation is given which analyzes the time of flight of each aircraftarrival/departure, the aircraft energy consumption, noise and airpollution, and the costs of air traffic control required for saleoperation. A.T.

A81-18087 The importance of 'Interim Standard Micro-wave Landing System' for small community airports. L. E. McCabe(Minnesota, Dept. of Transportation, St. Paul, Minn.). In: Interna-tional Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 2. NewYork, American Society of Civil Engineers, 1979, p. 618-621.

A81-18088 Airport/environs plan making - Managing theplanning process. R. R. Platzek (Williams, Platzek and Mocine,Sausalito, Calif.) and R. H. Doyle (Peak, Marwick, Mitchell and Co.,San Mateo, Calif.). In: International Air Transportation Conference,New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers,1979, p. 649-659.

Airport/environs planning should provide for the joint airport/environs institutional system, acceptable work program, adequatefinancing, public involvement, and a coordinated technical team. Itwas shown that a linear analytic approach to airport planning willinvolve only staff technicians who wiil recommend a final proposal;this is an in-house effort, which may make it possible to manageairport/environs planning even if the participants do not agree on thefinal selected plan. The cyclic or iterative method determineswhether a consensus exists, and repeats the process through anumber of cycles until the technicians, the public, and thedecision-makers agree on one feasible plan. The cyclic approach ismore applicable to situations involving low mutual thrust, requiringall participants to be familiar with all potential tradeoffs. A.T.

A81-18089 Runway Configuration Management Systemconcepts. A. N. Sinha and R. L. Fain (Mitre Corp., Air Transporta-tion Systems Div., McLean, Va.). In: International Air Transporta-tion Conference, New Orleans, La., April 30-May 3, 1979.Proceedings. Volume 2. New York, AmericanSociety of Civil Engineers, 1979, p. 668-683. U.S. Department ofTransportation Contract No. FA79WA-4184.

The Configuration Management System was based on threeconcepts representing a wide range of static and dynamic selectionprocesses. The basic model updates operational conditions such aswind and weather, checks on the availability of runways, andanalyzes feasible remaining available runways. The model outputprovides an ordered list of available runway configurations indecreasing order of capacity for a specific set of operating condi-tions; the intermediate model identifies feasible pairs of configura-tions (for current conditions and expected changes), and theadvanced model produces configurations for the extended period.The model testing at Chicago's O'Hare airport should result inenhancement such as interactions with vortex advisory systems,generation of equipment logs, and identification of relationshipsbetween dual and triple arrival configurations to assist in transitionbetween them. A.T.

A81 -18090 Traffic forecasting for the NRIA. M. A.Thomet and S. M. Sultan (Bechtel. Inc., San Francisco, Calif.). In:International Air Transportation Conference, New Orleans. La., April30-May 3, 1979, Proceedings. Volume 2. NewYork, American Society of Civil Engineers, 1979, p. 684-708.

A traffic forecasting method for the New Riyadh InternationalAirport was based on an econometric model which uses the value of

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imports of goods and services as a variable for predicting air traffic.The variable is projected by estimating petroleum revenues and theratio of imports to exports; the forecasts were made for 1983, 1990,and 2000. Historical statistics for passenger, air freight, and airmailare presented for the Saudi Arabia airports; it is noted that theeconometric model forecasts are under review and do not representthe present basis of planning. A.T.

A81-18091 Environmental aspects of airport planning. R.A. Waller (Atkins Research and Development, Epsom, Surrey,England). In: International Air Transportation Conference, NewOrleans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers,1979, p. 713-730. 25 refs.

The planning of airports around London is used to illustrateU.K. policy relating to the effects of airports on the environment.The background of legislation is described. Approaches to decision-making where environmental factors are important are compared,with particular reference to social-cost-benefit analysis. Possibletrends in environmental concern and in the environmental treatmentof airports are put forward for discussion. (Author)

AS1-18092 The role of aircraft separation assurance in thecockpit. F. C. White (Air Transport Association of America,Washington, D.C.). In: International Air Transportation Conference,New Orleans, La., April 30-May 3, 1979, Proceedings. Volume 2.

New York, American Society of Civil Engineers,1979, p. 743-751. 8 refs.

The application of an aircraft separation assurance display in thecockpit of a passenger aircraft is discussed. The principal method ofaircraft separation assurance will be provided by the ground airtraffic control (ATC) systems; the Discrete Address Beacon Systemand the Air Traffic Advisory and Resolution Service (DABS/ATARS)will supply a backup to the ATC in areas with an aircraft trafficdensity above 0.02 aircraft/sq mi. The Active BCAS which usesaltitude reporting air traffic control transponders will provide backupaircraft separation for the balance of the world airspace. The cockpitdisplay of airciaft separation is under investigation, but optimumcockpit display information has not yet been developed for installingthis system. A.T.

A81-18093 Saudi Arabia's new Gateway Airports. J. Hoytand R. Campbell (Ralph M. Parsons Co., Pasadena, Calif.). In:International Air Transportation Conference, New Orleans, La., April30-May 3, 1979, Proceedings. Volume 2. NewYork, American Society of Civil Engineers, 1979, p. 768-795.

A81-18100 */? Geometric dilution of precision in GlobalPositioning System navigation. B. T. Fang (Computer Sciences Corp.,System Sciences Div., Silver Spring, Md.). Journal of Guidance andControl, vol. 4, Jan.-Feb. 1981, p. 92-94. Contract No. NAS5-24300.

The evaluation of the GPS navigation performance is essentiallyequivalent to the computation of the diagonal terms of the geometricdilution of precision (GDOP) matrix. Certain theoretical resultsconcerning the general properties of the GDOP matrix are obtained.An efficient algorithm for the computation of the GDOP matrix andthe navigation performance index is given; and applications of theresults are illustrated by numerical examples. B.J.

Consideration is given to exact and approximate theories, computerexperiments, temporal and spatial normal-mode response, nonparallelflows, and nonlinear effects. Other concepts discussed includesecondary instability, coupling, and advanced perturbation methods.

VV.L.

A81-18122 Three-dimensional boundary layer transitionvia the mechanisms of 'attachment line contamination' and 'crossflow instability'. D. I. A. Poll (Cranfield Institute of Technology,Cranfield, Beds., England). In: Laminar-turbulent transition; Pro-ceedings of the Symposium, Stuttgart, West Germany, September16-22, 1979. Berlin, Springer- Verlag, 1980, p.253-262. 8 refs.

Transition via the mechanisms of attachment line contaminationand cross flow instability has been studied experimentally by using ahighly swept wing with a large leading edge radius. Although theprincipal objective was to determine the conditions necessary for theonset of turbulence, particular consideration has been given to the

identification of the forms of disturbance which occur in the laminarboundary layer before the turbulent spots appear. (Author)

A81-18318 Aeronautical-Maritime Engineering Satellite/AMES/ program of Japan. S. Miura, H. Morikawa (Ministry of Postsand Telecommunications, Radio Research Laboratories, Koganei,Tokyo, Japan), Y. Watanabe (Ministry of Transport, ElectronicNavigation Research Institute, Mitaka, Tokyo, Japan), and S.Morimoto (National Space Development Agency of Japan, Tokyo,Japan). International Astronautical Federation, International Astro-nautical Congress, 31st, Tokyo, Japan, Sept. 22-28, 1980, Paper80-D-171. 11 p.

A spin-stabijized geosynchronous satellite to be positioned overthe Pacific Ocean between 160 deg E long and 180 deg E long,AMES (Aeronautical Maintenance Engineering Satellite) is scheduledfor a 1986 launch by Japan. Developed by the National SpaceDevelopment Agency (NASDA), the cylindrical satellite 2 m inlength and 2 m in diameter weighs 350 kg BOL and carries an L-bandmultiple spot beam antenna to operate in the 5 GHz-5.25 GHz rangeas well as a global-beam C-band horn antenna transmitting at 1.5GHz/1.6 GHz. With an expected lifetime of 1.5 years, AMES willconduct navigation and communications studies within the jointAEROSAT program. Possible applications will be in the ATC andsmall fishing vessels communications domain. R.S.

A81-18371 A study of air breathing rockets - Subsonicmode combustion. G. Masuya, N. Chinzei, and S. Ishii (NationalAerospace Laboratory, Kakuda, Miyagi, Japan). International Astro-nautical Federation, International Astronautical Congress, 31st,Tokyo, Japan, Sept. 22-28, 1980, Paper 80-F-270. 1 5 p. 6 refs.

A study of subsonic mode combustion in cylindrical secondarycombustors of air-breathing rockets determined the effects of theoxidizer-fuel ratio of the primary rocket, mass flow ratio ofsecondary air to primary rocket propellants, and the length ofsecondary combustors. Gaseous hydrogen and oxygen were theprimary rocket propellants and room temperature compressed airwas used as secondary air. Combustion efficiency and air inletpressure were related to the ratio of experimental to theoretical exitpressure using a one-dimensional model which assumes incompletecombustion. A.T.

A81-18105 Dialogue on bridging some gaps in stabilityand transition research. T. Herbert (Stuttgart, Universitat, Stuttgart,West Germany) and M. V. Morkovin (Illinois Institute of Tech-nology, Chicago, III.). In: Laminar-turbulent transition; Proceedingsof the Symposium, Stuttgart, West Germany, September 16-22,1979. Berlin, Springer-Verlag, 1980, p. 47-72. 43refs. Research supported by the Alexander von Humboldt-Stiftung;Contract No. F49620-77-C-013.

Typical applied problems in stability and transition in external,internal, and free-shear layer through-flow systems are reviewed.

A81-18410 Satellites to aid flight safety. C. Rosetti (ESA,Paris, France). International Astronautical Federation, InternationalAstronautical Congress, 31st, Tokyo, Japan, Sept. 22-28, 1980,Paper80-1AA-17. 13 p.

A satellite-based system of communications for civil aviation isdiscussed. Changes in the present system are felt to be necessary; (1)because voice communication wastes the frequency spectrum; and(2) because many areas of the earth are not covered by radar. Theneed is stressed for an integrated system based on terrestrialinfrastructures over developed continental areas, and on satellites in

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ocean and desert areas for communication as well as for globalnavigation. Link budgets are given for a satellite-aircraft link having atransmission speed of 2400 bit/sec. The functions that could beperformed by an integrated L-band satellite system are enumerated.The simplifications that such a system would make possible arediscussed, as are the resulting improvements in safety. C.R.

A81-18497 ft Elimination of vibrations in aircraft pipingsystems (Ustranenie kolebanii v aviatsionnykh truboprovodakh). V.P. Shorin. Moscow, Izdatel'stvo Mashinostroenie, 1980. 160 p. 42refs. In Russian.

The book examines problems of designing acoustic dampers forpreventing vibrations in aircraft piping systems. Methods of com-puting damper effectiveness, design optimization, and experimentaltesting are presented. Simple designs of jet type, low frequencyacoustic filters, and resonating devices which prevent pipe and valvevibrations are described. AT.

A81-18576 ft Cruise-missile-carrier navigation requirements.G. T. Schmidt and R. H. Setterlund (Charles Stark Draper Laborato-ry, Inc., Cambridge, Mass.). Journal of Guidance and Control, vol. 3,IMov.-Dec. 1980, p. 487-493. 6 refs. Contracts No.F33657-78-C-0473; No. F33615-78-C-1563.

This paper addresses the modeling, simulation, and performancepredictions used in determining aircraft avionics and transfer-alignment requirements for a generic aircraft that would launchcruise missiles over water, a considerable distance from a firstTERCOM (terrain comparison) update area. Such would be the casefor an undefended wide-body aircraft that must remain far awayfrom an opponent's air defense system. This long standoff rangepresents some unique requirements that are not present in a missionwhere cruise missiles are launched 'close' to the first fix point, asfrom a penetrating bomber. The methodology used and the systemrequirements' results are described. (Author)

A81-18577 H Model-following system with assignable errordynamics and its application to aircraft. N. Kawahata (NationalAerospace Laboratory, Chofu, Tokyo, Japan). Journal of Guidanceand Control, vol. 3, Nov.-Dec. 1980, p. 508-516. 19 refs.

A main objective of this paper is to propose a practical tool fordesigning a model-following system. Successive differentiations ofoutput errors between a linear time-invariant system (a plant) and amodel yield controllable output error dynamics in a block-decoupledcompanion form. Such a particular form of the error dynamicsmakes it easy to determine a model-following control law such thatthe output error dynamics have arbitrarily assigned stability charac-teristics. Assigning asymptotic stability to the output error dynamicsalone does not guarantee system stability. The transmission zeroswhich are inherent to the input-output relations must be in theleft-hand half-plane for internal system stability. The approach hasbeen applied to a variable stability and response aircraft underdevelopment. An example of the longitudinal model-followingsystem on this aircraft is shown to demonstrate the proposedmethod. (Author)

A81-18578 H Frequency-shaped cost functional - Extensionof linear-quadratic-Gaussian design methods. N. K. Gupta (IntegratedSystems, Inc., Palo Alto, Calif.). Journal of Guidance and Control,vol. 3, Nov.-Dec. 1980, p. 529-535. 6 refs. Contract No.N00014-77-C-0247.

The linear-quadratic-Gaussian method for feedback controldesign is extended to include frequency-shaped weighting matrices inthe quadratic cost functional. This extension provides a means tomeet classical design requirements with automated computationalprocedures of modern control theory. A design algorithm tooptimize frequency-shaped cost functionals requires definition ofnew states and the solution of a modified linear-quadratic-Gaussianproblem. Four examples are presented to demonstrate frequencyshaping methodology: (1) aircraft in lateral wind, (2) an industrial

crane, (3) vibration control in helicopters, and (4) a system withtruncated modes. (Author)

A81-18599 # Radio navigation for aircraft: Handbook(Aviatsionnaia radionavigatsiia: Spravochnik). A. A. Sosnovskii and I.A. Khaimovich. Moscow, Izdatel'stvo Transport, 1980. 256 p. 36refs. In Russian.

The basic principles of air navigation instruments and systemsare described. Attention is given to loran, satellite navigationsystems, shoran, beacon landing systems (meter and centimeterwavelengths), radio altimeters, and Doppler velocity meters. B.J.

A81-18600 # Practical aerodynamics of the helicopter Mi-6A (Prakticheskaia aerodinamika vertoleta Mi-6A). K. N. Laletin andL. T. Artamonov. Moscow, Izdatel'stvo Transport, 1980. 168 p. 14refs. In Russian.

The book deals with some characteristic features of the rotorand airframe of the Mi-6A helicopter. The balancing, stability, andcontrollability of the helicopter in unsteady and some special modesof flight are examined. Attention is given to the behavior of thehelicopter in flights with a suspended load and in emergencysituations, such as failure of one of the two engines, failure of the tailrotor, etc. V.P.

A81 -18639 ft Turbine blade technology - Present and future.R. E. Allen and J. E. Sidenstick (General Electric Co., AircraftEngine Group, San Francisco, Calif.). American Society of Mechani-cal Engineers, Century 2 Aerospace Conference, San Francisco,Calif., Aug. 13-15. 1980,Paper80-C2/Aero-10. 7 p. Members, $1.50;nonmembers, $3.00.

Research being done on turbine blades and on the coolingsystems used in turbines is surveyed. Attention is given to theadvances that have been made in the CF6 turbine blade with theshaped gill holes used on recent CF6 designs and film cooling cited asexamples of cooling improvements. Attention is also given to the castcored design for blades. The benefits (among 'them corrosionresistance) offered by the alloy Rene' 80 are enumerated, and thegreater repairability of blades made possible by General Electric'sCODEP coating is discussed. The use of Hot Isostatic Pressing (HIP)to eliminate micro shrink is analyzed (the improvement in the CF6blade from this type of pressing being equivalent to a metaltemperature increase of approximately 25 F). Directional solidifica-tion is also discussed and the characteristics of new alloys (DS Rene'80H, Rene' 150, DS Eutectics) are presented. C.R.

A81-18640 I: Water content of helicopter gear oils. H. A.Spikes (Imperial College of Science and Technology, London,England) and P. B. Macpherson (Westland Helicopters, Ltd., Yeovil,Somerset, England). American Society of Mechanical Engineers,Century 2 International Power Transmissions and Gearing Confer-ence, San Francisco, Calif., Aug. 18-21, 1980, Paper 80-C2/DET-12.8 p. 13 refs. Members, $1.50; nonmembers, S3.00.

The dissolved water contents of a number of gearbox lubricantshave been measured in laboratory experiments, fatigue test rigs andhelicopter test and service gearboxes. The effect of temperature andhumidity on water content has been determined. It is concluded thatthe water levels present in test and service gearboxes may besufficient to reduce rolling fatigue lives. A comparison of watercontent in fatigue test rigs and service gearboxes shows thatdifferences exist between the two which may impair correlations offatigue lives. (Author)

A81-18642 ff A low height 2300 kW helicopter transmissionwith an enclosed planetary gear. G. White (Transmission Research,Inc., Cleveland, Ohio). American Society of Mechanical Engineers,Century 2 International Power Transmissions and Gearing Confer-ence. San Francisco, Calif., Aug. 18-21, 1980, Paper 80-C2/DET-17.6 p. Members, S1.50; nonmembers, S3.00.

A helicopter main rotor transmission with inputs from two

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1150-kW engines can be arranged to have the exceptionally lowheight of 32 cm. This low height, and consequent 10 percentreduction in weight, is made possible by the novel feature ofenclosing the final-stage planetary gear within the support walls andbearings of a large diameter spur gear. The three drive stages providean overall speed-reduction ratio of 81:1 at a main gearbox efficiencyof 97.5 percent. Additionally, the number of critical bearings in themain gearbox is reduced by 24 percent in comparison withproduction transmissions of similar rating. (Author)

A81-18646 ft Approximation of gear transmission error bystandard gear errors. A. Toda and G. V. Tordion (Universite Laval,Quebec, Canada). American Society of Mechanical Engineers, Centu-ry 2 International Power Transmissions and Gearing Conference. SanFrancisco, Calif., Aug. 18-21, 1980. Paper 80-C2/DET-71. 6 p. 5 refs.Members, S1.50; nonmembers, S3.00. Research supported by theNational Research Council of Canada.

The standard errors such as profile error, pitch error, etc. arecommonly measured through the existing gear testing machines.However, the gear transmission error is not measured as such,although it is a total error of the gear system and is a principalcontributor to the gearbox vibration. An attempt was made to relatethese individual errors to this important transmission error usingautomotive and gas turbine gears. The results show that thecombined pitch and profile error may be approximated as thetransmission error. (Author)

A81-18648 tj Experience with advanced high performancegear steel. S. Binder and J. C. Mack (Boeing Vertol Co., Philadelphia,Pa.). American Society of Mechanical Engineers, Century 2 Interna-tional Power Transmissions and Gearing Conference, San Francisco,Calif., Aug. 18-21, 1980, Paper 80-C2/DET-77. 7 p. 7 refs. Members,$1.50; nonmembers, S3.00.

A material development program is described that led to anadvanced, high-hot-hardness gear steel with improved load-carryingcapacity at elevated temperatures and under marginal lubrication.Development tasks included definition of scoring, bending fatiguestrength, and tooth contact capacities and fracture mechanicsproperties. Gears were load-run in test rigs and in endurancegearboxes. Since the gear steel is also used for bearing surfaces,rolling-contact fatigue tests were conducted. It has been found thatmelting practice has direct effects on fracture toughness and fatiguethreshold properties. Improved properties have been obtained bydouble-vacuum melting both the advanced steel and AISI 9310. Todate, over 100 tons of the advanced steel have been processed intohelicopter drive components. Approximately 27,000 hr of develop-ment, reliability and flight testing have been accomplished. Thematerial was selected for the gear train of the modernized U.S. ArmyCH-47D (Chinook) helicopter, for which qualification testing is nowcomplete. Improved characteristics will reduce maintenance andprovide increased reliability for this helicopter. (Author)

A81-18654 H The rigidity and performance of a simple spiralbevel helicopter gearbox. M. M. A. Taha, C. M. M. Ettles, and P. B.Macpherson (Imperial College of Science and Technology, London,England). American Society of Mechanical Engineers, Century 2International Power Transmission and Gearing Conference, SanFrancisco, Calif., Aug. 18-21, 1980, Paper 80-C2/DET-103. 10 p. 5refs. Members, $1.50; nonmembers, $3.00. Research supported bythe Ministry of Defence (Procurement Executive).

The analysis of Taha et al (1978) on the performance of ahelicopter gearbox with a cantilevered housing and two taper rollerbearings is extended to include a complete gearbox. The deflectionsat the tooth contact points must be determined precisely to providean even operation of spiral bevel gears; these deflections are afunction of the transmitted torque, bearing preloads, rigidity of thecasings and shafts, bearing spacings, and bearing alignment. Finally,the effects of misalignment between the bearing races, shaft andcasing, and spacer deformations are discussed. AT.

A81-18668 * *' Calculated and experimental data for a118-mm bore roller bearing to 3 million DN. H. H. Coe and F. T.Schuller (NASA, Lewis Research Center, Cleveland, Ohio). AmericanSociety of Mechanical Engineers and American Society of Lubrica-tion Engineers, Century 2 International Lubrication Conference, SanFrancisco, Calif.. Aug. 18-21, 1930, ASME Paper 80-C2/Lub-14. 8 p.16 refs. Members, SI .50; nonmembers, S3.00.

Operating characteristics for a 118-mm bore cylindrical rollerbearing were calculated using the computer program CYBEAN. Thepredicted results of inner and outer-race temperatures and heattransferred to the lubricant generally compared well with experimen-tal data for shaft speeds to 3 million DN (25,500 rpm), radial loadsto 8900 N (2000 Ib), and total lubricant flow rates to 0.0102 cum/min (2.7 gal/min). (Author)

A81 -18671 II On the steady state and dynamic performancecharacteristics of floating ring bearings. C.-H. Li and S. M. Rohde(GM Research Laboratories, Warren, Mich.). American Society ofMechanical Engineers and American Society of Lubrication Engi-neers, Century 2 International Lubrication Conference, San Francis-co, Calif., Aug. 18-21, 1980, ASME Paper 80-C2/Lub-17. 9 p. 13refs. Members, $1.50; nonmembers, S3.00.

An analysis of the steady state and dynamic characteristics offloating ring journal bearings has been performed. The stabilitycharacteristics of the bearing, based on linear theory, are given. Thetransient problem, in which the equations of motion for the bearingsystem are integrated in real time was studied. The effect of usingfinite bearing theory rather than the short bearing assumption wasexamined. Among the significant findings of this study is theexistence of limit cycles in the regions of instability predicted bylinear theory. Such results explain the superior stability characteris-tics of the floating ring bearing in high speed applications. Anunderstanding of this nonlinear behavior, serves as the basis for newand rational criteria for the design of floating ring bearings. (Author)

A81-18672 * # Performance of computer-optimized tapered-roller bearings to 2.4 million DN. R. J. Parker (NASA, LewisResearch Center, Cleveland, Ohio), S. I. Pinel, and H. R. Signer(Industrial Tectonics, Inc., Compton, Calif.). American Society ofMechanical Engineers and American Society of Lubrication Engi-neers, Century 2 International Lubrication Conference, San Francis-co, Calif., Aug. 18-21, 1980, ASME Paper 80-C2/Lub-18. 8 p. 5 refs.Members, $1.50; nonmembers, $3.00.

The temperature distribution and bearing heat generation of120.65 mm bore high-speed tapered roller bearings was determinedat shaft speeds of 20,000 rpm under simultaneous thrust and radialloads. The temperatures and thermal outputs were computed as

functions of shaft speed, loading lubricant flow rates, and lubricantinlet temperatures. Bearing temperatures and heat generation wereconsiderably lower than in standard bearings; cup cooling waseffective in lowering cup temperatures to levels of cone tempera-tures. A.T.

A81-18683 * ii Dynamic characteristics of a high-speed rotorwith radial and axial foil-bearing supports. L. Licht, W. J. Anderson(NASA, Lewis Research Center, Cleveland, Ohio), and S. W. Doroff(U.S. Navy, Office of Naval Research, Arlington, Va.). AmericanSociety of Mechanical Engineers and American Society of Lubrica-tion Engineers, Century 2 International Lubrication Conference, SanFrancisco, Calif., Aug. 18-21, 1980, ASME Paper 80-C2/Lub-35. 10p. 15 refs. Members, S1.50; nonmembers, $3.00. NASA-Navy-sponsored research.

An asymmetric rotor (19N; 4.3 Ib), supported radially andaxially by compliant bearings is subjected to severe excitation byrotating unbalance in the 'pitching' mode at speeds to 50,000 rpm.The resilient, air-lubricated bearings provide very effective damping,so that regions of resonance and instability can be traversed withamplitudes and limit-trajectories within acceptable bounds. A noveljournal bearing is introduced, in which a resilient support is furnishedby the outer turn of the coiled foil-element bent to form an openpolygon. The experimental apparatus and procedure are described.

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and the response of the rotor and flexible support system aredocumented by oscilloscope records of motion. (Author)

A81-18738 * ,-f Lubrication of rolling element bearings. R. J.Parker (NASA, Lewis Research Center, Cleveland, Ohio). AmericanSociety of Mechanical Engineers and American Society of Lubrica-tion Engineers, Century 2 International Lubrication Conference, SanFrancisco, Calif., Aug. 18-21, 1980, Paper. 24 p. 47 refs.

This paper is a broad survey of the lubrication of rolling-elementbearings. Emphasis is on the critical design aspects related to speed,temperature, and ambient pressure environment. Types of lubrica-tion including grease, jets, mist, wick, and through-the-race arediscussed. The paper covers the historical development, present stateof technology, and the future problems of rolling-element bearinglubrication. (Author)

A81-18748 Surface analysis of bearing steels after solventtreatments. II - Lubricant-coated bearing surfaces. M. K. Barnett(U.S. Navy, Naval Research Laboratory, Washington, D.C-). Ameri-can Society of Lubrication Engineers and American Society ofMechanical Engineers, International Lubrication Conference, SanFrancisco, Calif., Aug. 18-21, 1980, ASLE Preprint 80-LC-8A-6. 7 p.15 refs. Navy-sponsored research.

In order to evaluate the effectiveness of standard cleaningprocedures and individual solvents, reference surfaces of 440Cbearing steel were coated with thin films of a formulated synthetichydrocarbon or a formulated polyol ester instrument lubricant andexposed to the solvent cleaning process. The surfaces were thenanalyzed by wettability, Auger electron and X-ray photoelectronspectroscopies, and by Fourier transform infrared spectroscopy.Results are discussed in terms of cleaning efficiency, recontamina-tion, and types of random contamination. V.L.

A81 -18758 The wear of PTFE-containing dry bearingliners contaminated by fluids. R. W. Bramham, R. B. King, and J. K.Lancaster (Royal Aircraft Establishment, Farnborough, Hants.,England). American Society of Lubrication Engineers and AmericanSociety of Mechanical Engineers, International Lubrication Confer-ence, San Francisco, Calif., Aug. 18-21, 1980, ASLE Preprint80-LC-6B-3.9p. 15 refs.

The influence of fluid contamination on the wear of aircraft drybearing liners has been examined using an accelerated test procedure.It is shown that fluids generally increase wear to an extent dependingon the level of stress, the type of fluid and the structure andcomposition of the liner material. Water is deleterious, but at lowstresses mineral and diester oils can sometimes reduce the wear ratebelow that obtained in dry conditions. Explanations for the trendsobserved are deduced from an examination of worn surfaces byX-ray photoelectron spectroscopy and scanning electron microscopy.

(Author)

A81-18759 Ferrography as a health monitor and a designaid for the development of helicopter gearboxes. G. Pocock and S. J.Courtney (Admiralty Marine Technology Establishment, Poole,Dorset, England). American Society of Lubrication Engineers andAmerican Society of Mechanical Engineers, International LubricationConference, San Francisco, Calif., Aug. 18-21, 1980, ASLE Preprint80-LC-6B-4. 6 p. 9 refs.

The use of ferrography to monitor the health of helicoptergearboxes undergoing fatigue substantiation trials is described. Theresults illustrate the sensitivity of ferrography in detecting the onsetof gear fatigue and indicate that the fatigue was initiated bymicropitting. This suggests that the gears were not properlylubricated under the fatigue loads. (Author)

decision making, and observational control in the detection ofunexpectedly appearing objects and measurement of their parame-ters. Such situations may arise in astronomy, laser, sonar, and lidarobservations, recording of microparticles, etc. The analysis is carriedout within the framework of the theory of statistical solutions.Attention is given to practical aspects and to the effectiveness of theoptimal and suboptimal algorithms proposed for information pro-cessing and observation control. V.P.

A81-18777 Prediction methods for fatigue crack growth inaircraft material. J. Schijve (Delft, Technische Hogeschool, Delft,Netherlands). In: Fracture mechanics; Proceedings of the TwelfthNational Symposium, Washington University, St. Louis, Mo., May21-23, 1979. Philadelphia, Pa., American Societyfor Testing and Materials, 1980, p. 3-34. 41 refs.

The present state of knowledge of fatigue crack growth andqualitative and quantitative understanding of predictions are re-viewed with reference to the developments in experimental tech-niques and indications obtained from fatigue of aircraft structures.Results of recent work on the prediction of fatigue crack growth inaluminum alloys are reported, including (1) crack growth underflight-simulation loading with crack closure measurements, (2) crackgrowth predictions for flight-simulation loading based on a constantcrack opening stress level, and (3) crack growth under randomloading to explore the usefulness of the root mean square K-valueand to observe effects of irregularity and crest factor. V.L.

A81-19296 ft A fault tolerant multiprocessor system withreconfiguration suitable for multiaxial flight stabilization and trim-ming (Fehlertolerantes, rekonfigurierbares Mehrrechnersystem, geeig-net zur mehrachsigen Flugstabilisierung und -trimmung). D. Schmidt(Litton Technische Werke der Hellige GmbH, Freiburg im Breisgau,West Germany). Bundesministerium fur Forschung und Technologie,Statusseminar zur Luftfahrtforschung und Luftfahrttechnologie,Garmisch-Partenkirchen, West Germany, Oct. 8, 9, 1980, Paper. 12p. In German. Research supported by the Bundesministerium furForschung und Technologie.

This paper investigates a redundant processor system for timecritical process control with high reliability, fault tolerant proce-dures, and soft-wave control reconfiguration. Redundancy in theassemblies and the bus system of the hardware is discussed and thestructure of the computer system is presented for n identical andautonomous processors coupled with m serial bus connections. Across coupler consisting of several multiplexers is examined inrelation to configuration of the central processing units and thestorage units. A model for the software system which is subdividedinto a central unit and parallel operating functions is illustrated. R.C.

A81-19297 H Automatization of the adhesion process forsupporting airframe pans in light contour systems (AutomatisierterKlebeprozess fur tragende Flugzeug-Zellenbauteile in leichtenKontursystemen). H.-J. Rieckhof (Messerschmitt-Bolkow-BlohmGmbH, Hamburg, West Germany). Bundesministerium fur Forschungund Technologie, Statusseminar zur Luftfahrtforschung und Luft-fahrttechnologie, Garmisch-Partenkirchen, West Germany, Oct. 8, 9,1980, Paper. 19 p. In German.

This paper examines a simpler fixture along with automaticprocedures for a more economical construction of airframes. Thefixture consists of a light profile airframe and several milled or castmounting parts. The mass of the fixture is 190 kg compared to 700kg for previous fixtures and better pressure ratios in the adhesionjoints are obtained. An automatic quality control procedure based onthe Squirter inspection principle is also discussed. R.C.

A81-18773 # Detection of moving objects (Obnaruzheniedvizhushehikhsia ob'ektov). P. A. Bakut, lu. V. Zhulina, and N. A.Ivanchuk. Moscow, Izdatel'stvo Sovetskoe Radio, 1980. 288 p. 59refs. In Russian.

The book deals with the optimization of information processing.

A81 19298 ,7 A summary of proposals for airflight researchby the BMFT (Uberblick iiber die Fdrderung der Luftfahrtforschungdurch das BMFT). H. Hertrich (Bundesministerium fiir Forschungund Technologie, Bonn, West Germany). Bundesministerium fiirForschung und Technologie, Statusseminar zur Luftfahrtforschung

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und Luftfahrnechnologie, Garmisch-Partenkirchen, West Germany,Oct. 8, 9, 1980, Paper. 30 p. In German.

This paper examines the aims and distribution of governmentgrants by the Federal Department for Research and Technology(BMFT) for airflight research. Projects include investigations intointerference phenomena related to airfoil and lift, and carbon fibertechnology for civilian aircraft construction. Research into betterhandling of increased air traffic and cooperation in projects withother European countries and the U.S. are also discussed. Statisticson financial support for airflight research are reported for 1979 to1982. R.C.

A81 -19299 jf Stress measurements on landing gear for theAirbus A-300 B2 (Beanspruchungsmessungen am Fahrwerk desAirbus A-300 B2). O. Buxbaum (Fraunhofer-lnstitut fur Betriebs-festigkeit, Darmstadt, West Germany). Bundesministerium fiirForschung und Technologie, Statusseminar zur Luftfahrtforschungund Luftfahrnechnologie, Garmisch-Partenkirchen, West Germany,Oct. 8, 9, 1980, Paper. 20 p. 12 refs. In German.

This paper investigates operational characteristics of landing gearin relation to changes in aircraft design. The distinction between failsafe and safe line landing parts is discussed and preliminary resultswith an Airbus A-300 82 aircraft are presented. Measurement ofspring deflection of the landing gear stabilizer is discussed along withdetermination of the steering force on the nose end landing gear. Theeffect of increased rolling time on landing gear design is examinedalong with the torsion moment during the banking roll. R.C.

A81-19300 // Hingeless tailrotor in fiber composite construc-tion and vibration-isolation systems /ARIS, AS IS/ for helicopters(Gelenkloser Heckrotor in Faserverbund-Bauweise und Schwingungs-Isolationssysteme /ARIS, AS IS/ fiir Hubschrauber). G. Reichert(Messerschmitt-Bolkow-Blohm GmbH, Munich, West Germany).Bundesministerium fiir Forschung und Technologie, Statusseminarzur Luftfahrtforschung und Luftfahrnechnologie, Garmisch-Partenkirchen, West Germany, Oct. 8, 9, 1980, Paper. 35 p. 8 refs. InGerman. (MBB-UD-311-80-0)

The design of tailrotors and vibration isolation systems forhelicopters is discussed. Elastic bend-torsion elements are examinedin place of the hinge and bearings of the tail rotor, which provide areduction in weight, cost, and waiting time for operation. Emphasisis placed on determining the aerodynamic stability of the system forfull operation. The reduction of rotor induced cell vibration throughrotor isolation is also investigated. Passive units without additionalenergy input and active units with disturbance variable compensationare considered. R.C.

A81-19325 - Some aspects of optimizing the aerodynamicsof turbine stages (Problemy optymalizacji aerodynamicznej stopniaturbiny). R. Puzyrewski (Polska Akademia Nauk, Instytut MaszynPrzeplywowych, Gdansk, Poland). Instytut Maszyn Przeplywowych,Prace, no. 78, 1980, p. 101-108. In Polish.

The principal factors which define the efficient operation of aturbine stage are discussed, and the characteristic areas of kineticenergy dissipation are identified. A method of matching the guidewave and rotor blade systems for maximal stage efficiency isproposed. V.P.

A81-19335 ft Determination of the effect of transversecutouts on the hydrodynamic characteristics of a finite-span wing inthe case of steady and unsteady motion near a wall (K otsenkevliianiia poperechnykh vyrezov na gidrodinamicheskic koeffitsientykryla konechnogo razmakha pri statsionarnom i nestatsionarnomdvizhenii vblizi steoki). K. V. Rozhdestvenskii. Akademiia NaukSSSR, Izvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1980, p.122-128. In Russian.

A81 -19337 :; Characteristics of the velocity field near awing-body combination located at an angle of attack to an oncomingsupersonic flow (Osobennosti polia skorostei vblizi kombinatsii

krylo-korpus, raspolozhennoi pod uglom ataki k nabegaiushchemusverkhzvukovomu potoku). S. I. Kusakin. Akademiia Nauk SSSR,Izvestiia, Mekhanika Zhidkosti i Gaza, Nov.-Dec. 1980, p. 136-148.8refs. In Russian.

A theoretical study of the velocity field formed near awing-body combination in supersonic flow is presented;-the charac-teristics of the field related to the effects of the body (i.e., thefuselage) are emphasized. Attention is given to the general form ofthe singular term of the asymptotic expansion of the solution of thelinear equation in the vicinity of the Mach cone that starts at theintersection of the leading edge of the wing and the surface of thebody. A uniformly exact solution is obtained for the nonlineardifferential equation of additional velocity potential. The positionand location of the shock on the upper surface of the wing aredetermined. B.J.

A81 -19338 ;/' Propagation of three-dimensional acoustic per-turbations in channels of variable cross-sectional area at frequenciesdose to cutoff frequency (Rasprostranenie trekhmernykh akusti-cheskikh vozmushchenii v kanalakh peremennoi ploshchadi pope-rechnogo secheniia pri chastotakh, blizkikh v chastote otsechki). A.A. Osipov. Akademiia Nauk SSSR, Izvestiia, Mekhanika Zhidkosti iGaza, Nov.-Dec. 1980, p. 149-159. 8 refs. In Russian.

The paper presents a theoretical study of the propagation ofthree-dimensional acoustic disturbances in a two-dimensional gasflow in axisymmetric channels of variable cross-sectional area atfrequencies close to the cutoff frequency. Attention is given to slowchanges of cross-sectional area along the channel. The application ofthe WKB approximation to the present problem is considered, and amethod is developed for calculating the reflection coefficient of theacoustic disturbances. The present study may be applicable to theinvestigation of noise emission from jet engines. B.J.

A81-19342 SNIAS helicopters (Les helicopteres de laSNIAS). G. Bruner. L'Aeronautique et I'Astronautique, no. 84,1980, p. 21-30. 34 refs. In French.

The helicopters manufactured by the French firm SNIAS (theAerospatiale National Industrial Company) are reviewed. Specifica-tions, model types and brief commercial histories are presented forthe Alouette III, Super Frelon, Puma, Gazelle, Lama, Dauphin,Ecureuil and Super Puma. SNIAS facilities for helicopter productionand means employed for the fabrication of composite blades are alsopointed out. A.L.W.

A81-19344 The design-to-cost of aircraft (La conception acouts objectifs des avions). M. Tassinari (Societe Nationale Industri-elle Aerospatiale, Paris, France). L'Aeronautique et I'Astronautique,no. 84, 1980, p. 37, 38. In French.

The application of the design-to-cost approach to the manufac-ture and design of aircraft is examined. The various costs involved inthe production and utilization of an aircraft are reviewed, withattention given to development, industrialization, production andindirect costs borne by the manufacturer, the acquisition, utilization,maintenance and Hie cycle costs borne by the user, and the globalcost borne by all involved, and advantages of the design-to-costapproach in controlling global production costs while ensuringproduct quality are pointed out. The development of design-to-costin the United States as a means of controlling Defense Departmentcost overruns is then traced, and the use of a proposal procedurebased on minimal technical specifications and an imposed productioncost is emphasized. A.L.W.

A81-19346 Aircraft engine programs employing cost ob-jectives (Programmes de moteurs d'avions a objectifs de cout). C.Foure. L'Aeronautique et I'Astronautique, no.. 84, 1980, p. 41,43-48. In French.

Consideration is given to the procedures to be followed in aprogram of aircraft engine development, production and utilizationin which cost objectives are accorded the same importance as

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technical objectives. The practice of value analysis, which includesthe identification and ordering of user requirements, the identifica-tion of functions to be provided and the prediction of productioncosts, is discussed and illustrated for the case of the cycle definitionand scaling stage of engine airflow using the technique of massestimation. The roles of studies of technical and technologicalprogress, reliability and lifetimes, and maintenance requirements inengine development are considered, and measures which can be takenfollowing the initial design stage to reduce life cycle costs are pointedout. Finally, organizational structures developed for the carrying outof engine programs with cost objectives are examined. A.L.W.

A81-19347 Design to cost and new technologies (Designto cost et technologies nouvelles). F. Cordie (Avions Marcel-Dassault-Breguet Aviation, Direction Generale Technique, Saint-Cloud, Hauts-de-Seine, France). L'Aeronautique et I'Astronautique, no. 84, 1980,p. 49-55. In French.

The impact of the advent of new aircraft production technolo-gies on the design to cost process is discussed. The process ofdetermining the mass-cost relationship of a new constructiontechnology representing an improvement in aircraft weight and areduction in cost is considered, and design consequences of a weightreduction are pointed out. Consideration is then given to thedevelopment of composite material technology for military aircraft,and it is pointed out that the use of composites, which currentlyrepresent 35 to 40 percent of the mass of an advanced combataircraft, has lead to reductions in both aircraft mass and cost,particularly when the technology is considered in the design stage inthe design to cost process. A.L.W.

A81-19348 Pyrotechnics serving safety (La pyrotechnic auservice de la securite). S. Morlan (Societe Nationale IndustrielleAerospatiale, Division Systemes Balistiques et Spatiaux, UesMureaux, Yvelines, France). L'Aeronautique et I'Astronautique, no.84, 1980, p. 57, 59-61. 63-66. In French.

Possible applications of pyrotechnics technology capable ofimproving aircraft safety in the air and on the ground are examined.Consideration is given to the use of pyrotechnics in military aviationautomatic canopy jettisoning systems and pyrotechnic logic circuits,in civil aviation in the in-flight evacuation and protection system ofthe Corvette prototype aircraft, and in possible ground escapesystems for civil and commercial aircraft that have crashed. A.L.W.

decrease in drag is obtained with pneumatic turbulators that blowram air out of 0.6 mm pilot tubes at a distance of 16 mm. Thepneumatic models can be implemented at various positions and arealso found to be effective after the position of separation. R.C.

A81-19393 j Drag reduction through formation flight(Widerstandersparnis durch Formationsflug). D. Hummel and K.-W.Bock (Braunschweig, Technische Universitat, Braunschweig, WestGermany). Deutsche Gesellschaft fur Luft- und Raumfahrt, Sym-posium iiber Aerodynamischen Widerstand, Cologne, West Germany,Nov. 25, 26. 1980, Paper 80-106. 53 p. 12 refs. In German.

Improved performance through formation flying is examinedwith an estimation procedure. Reductions up to 20% of theperformance in solo flight are obtained. Total performance is shownto be dependent on the number and lateral distance of the aircraftand independent of the arrangement. The greatest reduction is foundtowards the center of the formation, and the optimal flight speed ofa formation of similar aircraft is less than that for a solo flight. Thereciprocal induction field with gliders at close distances is alsoinvestigated. R.C.

A81-19395 # Calculation of the lift dependent drag polar ofcambered fighter plane configurations with deflected maneuver flapsin the subsonic region by means of a modified procedure accordingto Lamar (Berechnung der auftriebsabhangigen Widerstandspolarenvon verwolbten Kampflugzeugkonfigurationen mit ausgeschlagenenManoverklappen im Unterschall an Hand eines modifizierten Verfah-rens nach Lamar). G. Wedekind (Dornier GmbH, Friedrichshafen,West Germany). Deutsche Gesellschaft fur Luft- und Raumfahrt,Symposium iiber Aerodynamischen Widerstand, Cologne, West Ger-many, Nov. 25,26, 1980, Paper 80-109. 15 p. In German.

A procedure to calculate lift and camber dependent drag isexamined in relation to the suction force analogy of Polhamus(1971) and a method by Lamar (1975, 1974) in which the suctionforces at the wing leading edge and side edge are calculated directlyand rotated vertical to the wing plane. The effects of a rounded-offnose and wing camber are also taken into account. A correctionmethod is derived for the polars of an uncambered wing-fuselagecombination along with modification for variations in the width ofthe nose region. In the case of cambered wings, the suction force isrotated vertical to the wing plane regardless of the nose camber forcalculating leading edge turbulence. R.C.

A81 -19375 System considerations in the implementationof digital control. K. C. Daly (Charles Stark Draper Laboratory, Inc.,Cambridge, Mass.). In: Guidance and control 1980; Proceedings ofthe Annual Rocky Mountain Conference, Keystone, Colo., February17-21, 1980. San Diego, Calif., Univelt, Inc.,1980, p. 651-664. 16 refs. (AAS 80-032)

The intent of this paper is to address several of the mostsignificant system requirements for digital controllers and to deter-mine how the processing system organization and performanceaffects these criteria. Special emphasis is given to control require-ments resulting from system configurations designed to produce highintegrity controllers. The resulting interaction between reliability andperformance considerations is also discussed. (Author)

A81-19392 H Reduction of profile drag by blowing outthrough peg holes in areas of streamline separation bubbles (Verrin-gerung des Profilwiderstandes durch Ausblasen aus Lochreihen imBereich laminarer Abloseblasen). K. H. Horstmann and A. Quast(Deutsche Forschungs- und Versuchsanstalt fur Luft- und Raumfahrt,Institut fiir Entwurfs-Aerodynamik, Braunschweig, West Germany).Deutsche Gesellschaft fur Luft- und Raumfahrt. Symposium iiberAerodynamischen Widerstand, Cologne, West Germany, Nov. 25, 26,1980, Paper 80-103. 18 p. In German.

This paper investigates the problem of streamline separationbubbles on aircraft profiles and fuselages. The additional drag isexamined in relation to increased angle of incidence and unusuallyhigh wall shear stress. A reduction in the separation bubble and a

A81-19396 H Procedures for optimal drag design of camberand flap deflection in supersonic regions with consideration togeometric limits (Verfahren zum widerstandsoptimalen Entwurf derWolbung und Klappenausschlage im Uberschall unter Beruck-sichtigung geometrischer Einschrankungen). G. Wedekind (DornierGmbH, Friedrichshafen, West Germany). Deutsche Gesellschaft fiirLuft- und Raumfahrt, Symposium iiber Aerodynamischen Wider-stand, Cologne, West Germany, Nov. 25, 26, 1980, Paper 80-110. 17p. In German.

This paper examines procedures for the optimization of camberin wing design of fighter planes. The method of Lagrange multipliersis presented for the camber optimization algorithm in the supersonicregion along with calculations for the determination of pressuredistribution and drag. An optimally cambered delta wing is illus-trated and the induced drag is compared to drag with and withoutsuction force. A method for combining individual wings with similardesign but different camber is also examined. R.C.

A81-19397 # Experimental investigation of a right anglewing with partially separated flow with and without ground effects(Experimentelle Untersuchung eines Rechteckfliigels bei teilweiseabgeloster Strbmung ohne und mit Bodeneinfluss). H. Bippes, M.Turk, and K. Jacob (Deutsche Forschungs- und Versuchsanstalt fiirLuft- und Raumfahrt, Gottingen, West Germany). Deutsche Gesell-schaft fiir Luft- und Raumfahrt, Symposium iiber AerodynamischenWiderstand, Cologne', West Germany, Nov. 25. 26, 1980, Paper80-111. 19 p. 6 refs. In German.

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This paper investigates ground effects on flight performancewith partially separated flow. Tests are carried out with a NACA4415 profile with an aspect ratio from 1.5 to 6.2. At smallerdistances higher pressure along the total wing chord is found in themiddle section of the pressure side of the wing with an increase inthe collection point of the suction side leading to an increase in lift.A net performance gain is registered despite an increase in the profiledrag. A secondary flow of low intensity is observed in the regionbetween the separated and adjoining flow. B.C.

ASM9398 H The practical application of the Wake BlockingCorrections according to Maskell (Die praktische Anwendung derWake Blocking-Korrekturen nach Maskell). H. Kamber (Eidge-nossisches Flugzeugwerk, Emmen, Switzerland). Deutsche Gesell-schaft fur Luft- und Raumfahrt, Symposium fiber AerodynamischenWiderstand, Cologne, West Germany, Nov. 25, 26, 1980, Paper80-112. 30 p. I n German. (FO-1533)

With the construction of larger wind channel models, walleffects play a greater role. This paper examines uncertainties foundin the Wake Blocking Correction method, particularly in reference tolarger models. Difficulties arise in the selection of the profileresistance and in the determination of the induced resistance whichcannot be obtained satisfactorily through measurement. A modifica-tion for calculating the profile resistance is presented along withvarious methods for determining the induced resistance. R.C.

A81-19399 # Drag estimations for stream-line and cylin-drical contour distortions on aircraft fuselages and train cars(Widerstandsabschatzung fur stromlinienformige und zylindrischeKonturstorungen an Rugzeugriimpfen und Eisenbahnwaggons). H.Neppert (Messerschmitt-Bolkow-Blohm GmbH, Hamburg, West Ger-many). Deutsche Gesel/schaft fur Luft- und Raumfahrt, Symposiumiiber Aerodynamischen Widerstand, Cologne, West Germany, Nov.25, 26, 1980, Paper 80-116. 17 p. 21 refs. In German.

This paper discusses drag estimations for cylindrical andaerodynamically stream-line bodies such as warning lights on aircraftfuselages and trains. Compressibility measurements in wind channelsare examined in relation to drag estimations. Cylindrical andstream-line warning light casings are compared for drag reduction andfuel conservation. The effect of the length of the boundary layer ondrag is investigated with casings on train wagons. R.C.

A81-19400 ff The determination of the induced drag on slimwings with high lift systems in the transonic region (Zur Ermittlungdes induzierten Widerstandes an schlanken Fliigeln mit Hochauf-triebssystemen im transsonischen Bereich). W. Sonnleitner(Messerschmitt-Bolkow-Blohm GmbH, Ottobrunn, West Germany).Deutsche Gesellschaft fur Luft- und Raumfahrt, Symposium iiberAerodynamischen Widerstand, Cologne, West Germany, Nov. 25, 26,1980, Paper. 27 p. 28 refs. In German. (MBB-FE122)

This paper investigates the effect of aircraft flaps with emphasison trail edge flaps. Potential theoretical methods for the calculationof flap effects are compared with semi-empirical handbook methods.A Gaussian least squares method is presented for approximation ofpolars near the crown and a formula for calculating the suctionpower explicitly is presented. The discrepancy between the calculat-ed K-values for the induced drag and experimental results is discussedalong with empirical correction functions. R.C.

A81-19417 Performance evaluation of an interrogation-reply scheduling technique for a discrete address beacon system. G.Bucci (CNR, Centre di Studio per I'lnterazione Operatore-Calcolatore, Bologna, Italy) and D. Maio (Bologna, Universita,Bologna, Italy). In: Digital signal processing.London and New York, Academic Press, 1980, p. 239-250. 8 refs.Research supported by the Consiglio Nazionale delle Ricerche.

Some results of a study carried out as part of an ATC projectsponsored by the Italian CNR are presented. The main objectiveswere to implement the ATC system on mini or microcomputers; togive an account of the maximum supported target load; and toachieve the greatest reliability of the surveillance and communication

functions performed by ATC. The structure of a real-time systemproposed for channel management is described; the major surveil-lance functions are developed, and a number of design criteria toreduce the associated computational effort are presented. Finally, anevaluation of interrogation-reply scheduling techniques is presented.

B.J.

A81 -19425 Characteristics of NAVSTAR user stations(Particularity des stations d'utilisateur du systeme NAVSTAR). G.David and J. P. Van Uffelen (Telecommunications Radio-Electriqueset Telephoniques, Le Plessis-Robinson, Hauts-de-Seine, France).L'Onde Electrique, vol. 60, Dec. 1980, p. 23-29. 7 refs. In French.

The characteristics of the NAVSTAR/GPS satellite navigationsystem are examined in relation to the operational requirements for auser station. Following a brief review of the NAVSTAR system andits advantages over previous navigation systems, consideration isgiven to the types of signals emitted by the 18 satellites in thesystem, their modulation and the C/A (clear acquisition) and P(protected) codes used for distance measurements. The synchroniza-tion of a local code with the received signal in the decoding of thetransmitted signal and the acquisition of time measurements by thesynchronization acquisition and tracking components of the receiveris discussed, and the functions and components of the user station,including antenna and preamplifier, receiver, and signal processor, areexamined. It is pointed out that the GPS offers users moving at highspeeds the possibility of determining their position with greateraccuracy than any other existing system of long-range navigation.

A.L.W.

A81-19441 « Experimental investigation of orographicwaves and vertical motions in the Krasnovodsk airport area (Eksperi-mental'nye issledovaniia orograficheskikh voln i vertikal'nykh dvizhe-nii v raione Aeroporta Krasnovodsk). 0. A. Liapina and E. I. Sofiev(Sredneaziatskii Regional'nyi Nauchno-lssledovatel'skii Institut,USSR). Meteoro/ogiia i Gidrologiia, Nov. 1980, p. 49-53. In Russian.

The difficult conditions for aircraft approach for landing instrong northerly winds were investigated. Orographic waves werestudied using constant level balloons tracked by double-theodoliteobservations; vertical motions were determined by conventionalpilot-balloon measurements. Wave parameters, their origins, and theireffects on aircraft landing approach conditions are presented. A.T.

A81 -19442 ti Conditions of generation and methods ofdamping the inlet vortex of a turbojet engine (Warunki generowania imetody tlumienia wiru wlotowego turbinowego silnika odrzutowe-go). T. Gajewski (Wuzsza Oficerska Szkola Lotnicza, Deblin, Poland).Technika Lotnicza i Astronautyczna, vol. 35, Nov. 1980, p. 5-8. 19refs. In Polish.

An aeromechanical analysis of the generation of an inlet vortexin a turbojet engine is presented. Methods for the prevention ofvortex generation and methods of vortex damping are described. B.J.

A81-19443 # Map-type displays (Wskazniki mapowe). Z.Mrotek (Instytut Lotnictwa, Warsaw, Poland). Technika Lotnicza iAstronautyczna, vol. 35, Nov. 1980, p. 11-16. 5 refs. In Polish.

The basic characteristics of map-type displays are described inorder to compile a classification of such devices. Particular attentionis given to the Decca Automatic Chart Display, the Decca Flight Log,the ACA Horizontal Situation Indicator, and the Ferranti CombinedMap and Electronic Display. B.J.

A81-19444 />' Calculation of propeller efficiency for an idealpropeller (Obliczenie sprawnosci smigla idealnego). Technika Lotnic-za i Astronautyczna, vol. 35, Nov. 1980, p. 25, 26. In Polish.

In the initial design of aircraft power plants, use is made of an'estimated' propeller characteristic which reflects correctly theinfluence of changes in such parameters as the propeller diameter, airdensity, etc. In the present paper, a method of deriving such acharacteristic is proposed. The solution obtained yields the upper

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bounds of the theoretical potentialities of propeller-type aircraftpower plants. V.P.

A81-19445 ft Collisions between aircraft and birds (Zderze-nia samolotow z ptakami). S. Tujaka (Przemyslowy Instytut Tele-komunikacji, Gdansk, Poland). Technika Lotnicza i Astronautyczna,vol. 35, Nov. 1980, p. 27, 28. In Polish.

The danger that birds pose for aircraft is described. Attention isgiven to the flight altitudes of various species of birds, types of birdflight, and methods of preventing collisions between aircraft andbirds in the vicinity of airfields. B.J.

A81-19469 Circulation Control Wing /CCW/ flight tests. C.Sewell (Grumman Aerospace Corp., Bethpage, N.Y.). Society ofExperimental Test Pilots, Technical Review, vol. 15, no. 1, 1980, p.6-20.

The Circulation Control Wing (CCW) design, based on theCoanda effect, involves the conversion of the trailing edge of theairfoil into an enlarged rounded surface to which a jet of air adhereswhen blown tangentially from the upper surface. The resulting highaugmentation of circulation lift reduces landing approach andtakeoff velocities and distances, and offers options for increasedaircraft payload and wing loading. The aerodynamic technology forthe CCW program was developed by the NSRDC. A contract for thedesign and modification of an A-6A aircraft to the CCW configura-tion and subsequent flight testing was awarded to Grumman in 1977.Flight testing began Jan. 29, 1979 and was completed Mar. 1, 1979in 16 flights for a total of 25 hours. P.T.H.

A81-1947Q Planning for and evaluating the potential of aland based aircraft for carrier operations. P. S. Norton (Lockheed-California Co., Burbank, Calif.). (Society of Experimental TestPilots, European Symposium, 11th, Bristol, England, Apr. 1979.1Society of Experimental Test Pilots, Technical Review, vol. 15, no.1,1980, p. 21-35.

The role of the test pilot in performing a compressed and fairlycomplicated shore-based carrier suitability evaluation of a land-basedaircraft is considered. Particular attention is given to an evaluationwhich Lockheed conducted with the Dassault/Dornier Alpha Jet atIstres, France; the evaluation is examined through the test pilot'sviewpoint, with emphasis on the test pilot's personal role andcontribution to the overall effort. The evaluation is relatively uniquebecause it has served to measure the potential of a land-based aircraftfor carrier operations without operation from an actual aircraftcarrier. Several primary facilities, such as a mirror landing system,adjustable angle of attack system, and telemetry, were required.

P.T.H.

A81-19471 * A status report on NASA general aviationstall/spin flight testing. J. M. Patton, Jr. (NASA, Langley ResearchCenter, Hampton, Va.). Society of Experimental Test Pilots, Tech-nical Review, vol. 15, no. 1, 1980, p. 36-49. 9 refs.

The NASA Langley Research Center has undertaken a compre-hensive program involving spin tunnel, static and rotary balance windtunnel, full-scale wind tunnel, free flight radio control model, flightsimulation, and full-scale testing. Work underway includes aero-dynamic definition of various configurations at high angles of attack,testing of stall and spin prevention concepts, definition of spin andspin recovery characteristics, and development of test techniques andemergency spin recovery systems. This paper presents some interest-ing results to date for the first aircraft (low-wing, single-engine) inthe program, in the areas of tail design, wing leading edge design,mass distribution, center of gravity location, and small airframechanges, with associated pilot observations. The design philosophy ofthe spin recovery parachute system is discussed in addition to testtechniques. P.T.H.

ASM9490 Industry proposes supersonic V/STOL. C. A.Robinson, Jr. Aviation Week and Space Technology, vol. 114, Jan.12, 1981, p. 36-39, 42.

A joint supersonic V/STOL fighter development and flightdemonstration program is being proposed by McDonnell Douglas andRolls-Royce. The proposed flight demonstration aircraft is based onthe use of a modified Marine/British Aerospace AV-8A airframe andthe Rolls-Royce Pegasus 11 engine to increase overall engine thrustby 50%. The four-to-five year development and flight demonstrationprogram would produce an aircraft capable of flight in the Mach 1.6region and would cost 300-500 million dollars. By using the STOLcapability, USAF aircraft could be airborne in approximately 1200ft, carrying a full load of ordnance. Mission capabilities include closeair support and interdiction. P.T.H.

A81-19491 Solid-state power system use expands. P. J.Klass. Aviation Week and Space Technology, vol. 114, Jan. 12, 1981,p. 70, 71, 73.

Variable-speed constant-frequency (VSCF) systems for supply-ing aircraft electric power are challenging more traditional hydro-mechanical constant-speed type systems for military applicationsafter nearly two decades of development. The potential appeal ofVSCF is the reduction of moving parts, which holds promise ofhigher reliability and reduced maintenance. It also offers moreprecise control of frequency and voltage, and responds more quicklyto large electric load changes to minimize voltage and frequencytransients. The operational payoff in terms of increased avionicsreliability is difficult to measure, however. This paper examinesapplications of VSCF, with particular attention given to the 40-kvasystem that Westinghouse will supply for the F-5G (the system isexpected to be scaled-up version of its 20-kva dc link systemdesigned for the AV-8B). P.T.H.

A81-19497 Fighters for the 1990s. M. Lambert. Interavia,vol. 36, Jan. 1981, p. 19-26.

Programs under way in the U.S., Britain, West Germany, andFrance to design fighter aircraft for the 1990's are surveyed noting

that the principles of survivability, lethality, and affordability areparamount. The stealth concept is illustrated through a diagram ofthe Tactical High Altitude Penetrator. Various concepts that willfigure in fighter design are presented, among them the supercruiser,forward sweep, and the Advanced Fighter Technology IntegratorAFTI/F-16 (offering six-degree-of-freedom flight). The AFTI/F-111Mission Adaptive Wing, with flexible plastic skin on the upper wingsurface and special internal control linkages, is discussed, as is theHiMAT Highly Maneuverable Aircraft Technology demonstrator(performance design point, Mach 0.9 at 30,000 ft; maximum speed,more than Mach 1.5; able to pull 6G at Mach 1.2 at 30,000 ft).Attention is also given to runway dependence, integrated avioniccontrol, and propulsion to Integrated Flight/Fire Control. C.R.

A81-19498 Primary training of military pilots - Changingtheories and new trainers. M. Grangier. Interavia, vol. 36, Jan. 1981,p. 29-33.

The need to choose between propeller, turboprop, and jetaircraft for the primary training of military pilots is discussed withhigh fuel costs cited as one of the factors limiting flight training. It isnoted that turboprops seem to be growing in favor since they make itpossible to give pilots more advanced training. They can be used notonly to train pilots in the classical missions of primary training (basictraining, conversion) but also to give them experience in instrumentflying, navigation with IFR equipment for day/night observation,aerobatics, and formation flying. Training aircraft under develop-ment in various countries are discussed, including the AerospatialeEpsilon, the Caproni Vizzola C-22J, the Embraer EMB-312, theGulfstream American Peregrine 600, and the SIAI-Marchetti S.211and SF.260TP. C.R.

A81-19499 Visual systems at Lufthansa's simulator centre.J. Gegerle. Interavia, vol. 36, Jan. 1981, p. 42, 43.

The high cost of in-flight pilot training has spurred thedevelopment of simulators in civil aviation. Lufthansa's experiencewith simulators is discussed, with attention given to recent improve-

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ments. Redifon's Daynite, a daylight Computer Generated Imagerysystem, is analyzed, as is the newer IMovoview SP2 system. The lattercan offer night scenes having as many as 5,000 light points anddaylight scenes having a large number of surfaces. Economicincentives will ensure the continued development of simulators:Lufthansa estimates that it costs $12,360 for one flight hour on a747, compared with $515 for the same time in a simulator. C.R.

A81-19500 The flying hologram - Latest in head-updisplay systems. D. Boyle. Interavia, vol. 36, Jan. 1981, p. 44, 45.

The holographic or diffractive optics head-up display (D-HUD)is analyzed. This new equipment uses holographic principles toprovide a head-up display with a wider field of view and improvedbrightness for the symbols that are presented to the pilot super-imposed on his view of the outside world. The different types ofoptical path for the D-HUD system are presented diagramatically.With holographically produced lenses, symbol brightness is improvedfrom 1,600 to 5,000 ft-Lamberts and raster presentation brightness israised from 400 to 1,200 ft-Lamberts. The use of the D-HUD in theU.S. Air Force's Low Altitude Navigation Targeting Infra-Red forNight (LANTIRN) program is discussed. C.R.

A81-19552 H Model vibrations beyond low-speed stall(Vibrations de maquettes au-dela du decrochage a basse vitesse). X.Vaucheret (ONERA, Chatillon-sous-Bagneux, Hauts-de-Seine,France). La Recherche Aerospatiale, Nov.-Dec. 1980, p. 387-397. 5refs. In French.

Vibrations of a string-mounted model beyond stall are analyzedby using the nonlinear equation of motion established for moderateamplitudes around high angle of attack according to a time/angle ofattack cycle. The nonlinear solution yields frequency and dampingvariations versus amplitude and amplitude history beyond stall. Aparametric study shows that the effects of maximum angle of attackand the duration of the step at this angle are decisive. For hard stall,the operator can perform the tests from indications that are aimed atavoiding amplitude divergences at nonzero frequency. B.J.

A81 -19629 Nonlinear aerodynamic characteristics of athin airfoil of arbitrary plane configuration. S. M. Belotserkovskiiand M. I. Nisht. (Aeromekhanika. Sbornik statei posviashchaetsia60-letiiu so dnia rozhdeniia akademika Vladimira Vasil'evichaStruminskogo, p. 9-24.) Fluid Mechanics - Soviet Research, vol. 9,Mar.-Apr. 1980, p. 1-13. 26 refs. Translation.

General approaches to the schematization of separated inviscidincompressible flows are reviewed, along with numerical methods ofsolving the flow equations. Nonlinear and nonstationary problemsconcerning separated flows are described on the basis of thethree-dimensional Laplace equation, the conditions at wing surfaceand the vortex sheet, and the initial conditions. The behavior of thewakes in space and time is determined from differential equationsresulting from the condition that the vortex sheet must move alongthe trajectory of the fluid particles. The mechanical load over thewing is computed by means of the Cauchy-Lagrange integral. Amethod of discrete vortices is used to implement the scheme on acomputer, and an example is considered in which the vortexstructures and nonlinear aerodynamic coefficients of rectangular anddelta wings are determined for separated and nonseparated flows.

A.Y.

A81-19630 Thin minimum-drag airfoils. V. N. Zhigulev.(Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu so dniarozhdeniia akademika Vladimira Vasil'evicha Struminskogo, p.24-31.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, p.14-19. Translation.

The variational problem of 'returned' suction force on acambered slender wing is analyzed and solved for a class of infiniteslender wings of arbitrary planform in a gas flow at small angles ofincidence in nonlinear regime. The requirement that the leading edgeof the wing be shock-free is shown to be necessary for a completeimplementation of the suction force. Various methods are proposed

for the determination of the optimal distribution of the wingcambers for subsonic and transonic flight velocities. A.Y.

A81-19631 The coordinate-deformation method in theproblem of a supersonic gas flow over an airfoil. S. I. Kusakin and M.F. Pritulo. (Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiuso dnia rozhdeniia akademika Vladimira Vasil'evicha Struminskogo,p. 32-39.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980,p. 20-26. Translation.

The essentially three-dimensional flow field at a delta wingsituated in a supersonic gas flow is examined. It is shown that asingularity generated by the breaking point on the leading edge arisesin the pressure gradient of the wing surface. The general form of thissingularity is determined. The method of deformed coordinates isused to obtain an exact solution of the differential equation for theadditional velocity potential. A.Y.

A81-19632 Hypersonic gas flow over a delta wing. A. I.Golubinskii and A. I. Shchedrin. (Aeromekhanika. Sbornik stateiposviashchaetsia 60-letiiu so dnia rozhdeniia akademika VladimiraVasil'evicha Struminskogo, p. 39-45.) Fluid Mechanics - SovietResearch, vol. 9, Mar.-Apr. 1980, p. 27-32. 9 refs. Translation.

The problem of a plane delta wing of moderate aspect ratio in ahypersonic gas flow, whose freestream Mach number tends toinfinity as the adiabatic index tends to zero is examined. The analysisis carried out for small angles of attack. An asymptotic expressionfor the pressure at the center of the Mach cone is derived. A.Y.

A81 -19633 Some characteristics of subsonic flow over the

root area of a sweptback wing. M. N. Nekrasova. (Aeromekhanika.Sbornik statei posviashchaetsia 60-letiiu so dnia rozhdeniia akademi-ka Vladimira Vasil'evicha Struminskogo, p. 46-55.) Fluid Mechanics -Soviet Research, vol. 9, Mar.-Apr. 1980, p. 33-40 5 refs. Translation.

Flows past peaked profiles at the root of a swept wing and atthe sections of a straight wing are studied by visualization tech-niques, and the pressure distribution is determined. Two types offlow were observed: flow with an almost complete isentropiccompression of the supersonic flow along the surface of a swepttransonic wing; and flow with partially isentropic compression, witha shock-wave at the wing root. A.Y.

A81-19634 Plane vortex gas flows. A. A. Nikol'skii.(Aeromekhanika. Sbornik statei posviashchaetsia 60-letiiu so dniarozhdeniia akademika Vladimira Vasil'evicha Struminskogo, p.55-66.) Fluid Mechanics - Soviet Research, vol. 9, Mar.-Apr. 1980, p.41-50. 5 refs. Translation.

The two-dimensional turbulent gas flow equations are studiedby expressing them in a convenient form. Two dual laws areestablished for subsonic flows: (1) under constant pressure, the angleof inclination of the velocity vector varies monotonously along thepressure line; (2) with constant inclination of the velocity vector, thepressure varies monotonously along the velocity vector line. Theselaws are used to investigate the uniqueness of the location of theshock-waves in supersonic flows of two-dimensional tapered bodieswith angles of inclination not exceeding a critical value. A.Y.

A81-19636 The sonic boom from an aircraft flying alongan arbitrary path in a stratified atmosphere in the presence of athree-component wind. lu. L. Zhilin. (Aeromekhanika. Sbornik stateiposviashchaetsia 60-letiiu so dnia rozhdeniia akademika VladimiraVasil'evicha Struminskogo, p. 73-86.) Fluid Mechanics • SovietResearch, vol. 9, Mar.-Apr. 1980, p. 57-68. 19 refs. Translation.

General theory of acoustic shock is applied to the study of theacoustic shock from an aircraft flying in a layered atmosphere with athree-component wind, all the parameters of which depend only onthe altitude above the earth's surface. Calculation of attenuationfactors is reduced to four quadratures. It is shown that for a givenstate of the atmosphere the attenuation factors depend on only five

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similarity parameters, characterizing the flight regime and theposition of the observer perceiving the acoustic shock relative to theflight path. P.T.H.

A81-19643 The influence of flow disturbances on thelaminar-turbulent transition in a supersonic boundary layer. A. M.Kharitonov (Akademiia Nauk SSSR. Institut Teoreticheskoi iPrikladnoi Mekhaniki, Novosibirsk, USSR). (Aeromekhanika.Sbornik statei posviashchaetsia 60-letiiu so dnia rozhdeniia akademi-ka Vladimira Vasil'evicha Struminskogo, p. 153-164.) Fluid Mechan-ics - Soviet Research, vol. 9, Man-Apr. 1980, p. 125-134. 18 refs.Translation.

Results of experimental studies on the effect of various factorson the transition of a supersonic boundary layer are discussed. It isshown that in supersonic wind tunnels, a significant effect on thetransition of the boundary layer on a model is exerted by the scale ofacoustic perturbations, which is proportional to the boundary layerdisplacement thickness of the working section. Experimental dataobtained over a wide range of variation of flow parameters inaerodynamically similar test installations with different dimensionsof the working section are generalized by means of a correlationparameter based on the disolacement thickness. P.T.H.

A81 -19644 Wall cooling and the laminar-turbulent bound-ary layer transition at supersonic flow velocities. M. A. Alekseev, V.A. Kuz'minskii, N. F. Ragulin, and lu. G. Shvalev. (Aeromekhanika.Sbornik statei posviashchaetsia 60-letiiu so dnia rozhdeniia akademi-ka Vladimira Vasil'evicha Struminskogo, p. 164-170.) Fluid Mechan-ics - Soviet Research, vol. 9. Mar.-Apr. 1980, p. 135-139. Translation.

Results of an experimental investigation of the effect of coolingthe surface on the transition of a boundary layer from a turbulent toa laminar to a turbulent one on straight wing models and bodies ofrevolution with ogive nose in a supersonic wind tunnel are discussed.The flow velocities corresponded to Mach numbers of 3, 3.5, and 4,and the Reynolds number ranged from 18 million to 40 million. Thephenomenon of reversal is seen to be characteristic of turbulenttransition under these conditions. P.T.H.

A81-19657 Nondestructive dynamic testing. E. M. Uygur(Middle East Technical University, Ankara, Turkey). In: Researchtechniques in nondestructive testing. Volume 4.London, Academic Press, 1980, p. 205-244. 117 refs.

Recent advances in nondestructive dynamic testing based ondamping and resonant frequency measurements are reviewed withreference to the underlying theory, applications, and instrumenta-tion. Examples which illustrate the application of dynamic testingtechniques to the study and detection of both macroscopic andmicroscopic defects and properties are given. It is shown that in mostcases the same arrangement and instrumentation can be employedfor both micro- and macro-scale work. V.L.

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STAR ENTRIES

N81-13916# Southern California Association of Governments.Los AngelesSOUTHERN CALIFORNIA AVIATION SYSTEM STUDYTechnical Report. 1978 - 1980Lawrance H. Goldman, J. Timothy Merwin. Lisa D. Murphy, andWalter E. Gillfillan Jul. 1980 237 p refs(PB80-215544) Avail: NTIS HCA11 /MFA01 CSCL 13B

Southern California's 1995 air travel needs are examined.Existing and planned air carrier airports are restricted by policyconstraints and cannot accommodate the air travel demandforecast for 1995. Seven overall strategies, joint civilian/ militaryuse of an existing military facility, removal or revision of thepolicy constraints, a new air carrier airport are described.Alternative airport sites are evaluated for market attractiveness,noise impacts, airspace workability, financial feasibility, etc. GRA

N81-13917*# New Mexico Univ.. Albuquerque. TechnologyApplication Center.A IRCRAFT MAINTENANCE. CITATIONS FROM THEINTERNATIONAL AEROSPACE ABSTRACTS DATA BASEProgress Report. 1974 - Jul. 1980Gerald F. Zollars Sep. 1980 84 p Supersedes NTIS/PS-79/0859/3 Sponsored in cooperation with NASA and NTIS(NASA-CR-163837; PB80-815905: NTIS/PS-79/0859/3)Avail: NTIS HC S30.00/MF $30.00 CSCL 018

These citations from the international literature concernvarious aspects of aircraft maintenance. Both military and civilaviation experience are included. Articles cited concern airlineoperations, engine and avionics reliability, the use of automatictest equipment, maintenance scheduling, and reliability engineer-ing. This updated bibliography contains 347 citations, 85 of whichare new additions to the previous edition. GRA

N81-13918*|f National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.WIND-TUNNEL TEST OF AN ARTICULATED HELICOPTERROTOR MODEL WITH SEVERAL TIP SHAPESJohn D. Berry and Raymond E. Mineck Dec. 1980 95 p refsPrepared in cooperation with Army Aviation Research andDevelopment Command. Hampton. Va.(NASA-TM-80080: L-12774: AVRADCOM-TR-79-49) Avail:NTIS HC A05/MF A01 CSCL 01A

Six interchangeable tip shapes were tested: a square (baseline)tip. an ogee tip. a subwing tip. a swept tip. a winglet tip. and ashort ogee tip. In hover at the lower rotational speeds the swept,ogee, and short ogee tips had about the same torque coefficient,and the subwing and winglet tips had a larger torque coefficientthan the baseline square tip blades. The ogee and swept tipblades required less torque coefficient at lower rotational speedsand roughly equivalent torque coefficient at higher rotationalspeeds compared with the baseline square tip blades in forwardflight. The short ogee tip required higher torque coefficient athigher lift coefficients than the baseline square tip blade in theforward flight test condition. Author

N81-13920*# Boeing Commercial Airplane Co.. Seattle. Wash.A SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSISOF SUPERSONIC AIRCRAFT. PART 2: USER'S MANUALFinal Contractor Report. Sep. 1978 - Aug. 1980W D. Middleton. J. L. Lundry, and R G. Coleman WashingtonDec. 1980 124 p refs

(Contract NAS1-15534)(NASA-CR-3352: D6-41840-2) Avail: NTISHC A06/MF A01 CSCL01C

The system uses linearized theory methods for the calculationof surface pressures and supersonic area rule concepts incombination with linearized theory for calculation of aerodynamicforce coefficients. Interactive graphics were included in the systemto display or edit input and to permit monitoring and readout ofprogram results. T.M

N81 13921*# National Aeronautics and Space AdministrationLangley Research Center. Hampton, Va.A COMPUTER PROGRAM FOR THE DESIGN AND ANALY-SIS OF LOW-SPEED AIRFOILS. SUPPLEMENTRichard Eppler (Stuttgart Univ.) and Dan M Somers Dec. 198030 p refs(NASA-TM-81862) Avail: NTIS HC A03/MF A01 CSCL01A

Three new options were incorporated into an existingcomputer program for the design and analysis of low speedairfoils. These options permit the analysis of airfoils having variablechord (variable geometry), a boundary layer displacement iteration,and the analysis of the effect of single roughness elements. Allthree options are described in detail and are included in theFORTRAN IV computer program. Author

N81-13922*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.PASSIVE CONTROL OF WING/STORE FLUTTERWilmer H. Reed. III. F. W. Cazier. Jr.. and Jerome T. Foughner.Jr. Dec. 1980 19 p refs Presented at the 5th Joint Tech.Coordinating Group Aircraft Stores Compatibility Symp.. St. Louis.9-11 Sep. 1980(NASA-TM-81865: L-14010) Avail: NTIS HC A02/MF A01CSCL 01A

Results are presented for a passive flutter suppressionapproach known as the decoupler pylon. The decoupler pylondynamically isolates the wing from store pitch inertia effects bymeans of soft spring/damper elements assisted by a low frequencyfeedback control system which minimizes static pitch deflectionsof the store because of maneuvers and changing flight conditions.Wind tunnel tests and analyses show that this relatively simplepylon suspension system provides substantial increases in flutterspeed and reduces the sensitivity of flutter to changes in storeinertia and center of gravity. Flutter characteristics of F-16 andYF-17 flutter models equipped with decoupler pylon mountedstores are presented and compared with results obtained on thesame model configuration with active flutter suppression systems.These studies show both passive and active concepts to beeffective in suppressing wing/store flutter. Also presented aredata showing the influence of pylon stiffness nonlinearities onwing/store flutter. Author

N81-13923*# Bihrle Applied Research. Inc., Jericho. N. Y.ROTARY BALANCE DATA FOR A SINGLE-ENGINEAGRICULTURAL AIRPLANE CONFIGURATION FOR ANANGLE-OF-ATTACK RANGE OF 8 DEG TO 90 DEC FinalReportWilliam Mulcay and Julio Chu Washington NASA Dec. 1980243 p refs(Contract NAS1-14849)(NASA-CR-3311) Avail: NTIS HCA11 /MFA01 CSCL 01A

Aerodynamic characteristics obtained in a helical flowenvironment utilizing a rotary balance located in the Langleyspin tunnel are presented in plotted form for a 1/10 scale singleengine agricultural airplane model. The configurations testedinclude the basic airplane, various wing leading edge and wingtip devices, elevator, aileron, and rudder control settings, andother modifications. Data are presented without analysis for anangle of attack range of 8 deg to 90 deg. and clockwise andcounter-clockwise rotations covering a spin coefficient range from0 to .9. Author

N81-13925$ Aeronautical Research Inst. of Sweden. Stockholm.Aerodynamics Dept.DOWNWASH CALCULATION AT CLOSE RANGE BEHINDA TRAPEZOIDAL WING IN SUPERSONIC FLOW

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Anders Hasselrot 1980 37 p refs(Contract FMV-F-K-80123-78-017-21-001)(FFA-TN-AU-1661: ISSN-SW-0081-5640) Avail: NTISHC A03/MF A01

The results were determined as a function of values at thewing trailing edge and at the Trefftz-plane. A correction for offthe wing plane points is given. A description of the method, aFORTRAN listing of the coded method and results to be comparedwith theoretical and experimental values of downwash arepresented. T.M.

N81-13926# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany). Abt.Rettungs-und Bergungssysteme.A CONTRIBUTION TO STABILIZATION OF FLIGHT VEHICLEPARACHUTE SYSTEMSChristos Saliaris and Dieter Muenscher Apr. 1980 34 p refsIn GERMAN: ENGLISH summary Report will also be announcedas translation (ESA-TT-679)(DFVLR-Mitt-80-05) Avail: NTIS HC A03/MF A01: OFVLR.Cologne DM 8.30

The dynamic behavior of the two dimensional motion of aparachute load system was considered. For a mathematical model,the system of nonlinear differential equations was numericallyintegrated without linearization. For a number of examples witha modified guide surface parachute, the influence of the canopysize, the distance between the attachment point and thecanopy, and the distance between the attachment point and thecenter of gravity of the load on the oscillation of the flightvehicle was studied. T.M.

N81-13929# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Goettingen (West Germany). Abt.Instationaere Aerodynamik.ANALYSIS OF UNSTEADY PRESSURE MEASUREMENTSON AN AEROFOIL SECTION WITH AN HARMONICALLYOSCILLATING. SLOTTED FLAPKarl Kienappel and David F. Round (MBB. Hamburg) Apr. 198066 p ref(DFVLR-FB-80-22) Avail: NTIS HC A04/MF A01: DFVLR.Cologne DM 14.20

An analysis is made of unsteady pressure distribution andaerodynamic coefficients measured for an airfoil and harmonicallyoscillating slotted control surface in a low speed wind tunnel.The influences on the pressure distribution and aerodynamiccoefficients are examined: frequency of oscillation: flap steadydeflection: section incidence: flow velocity and slot geometry,i.e. whether the slot is open or closed. There is a carry overbetween steady and unsteady pressure distributions, whichalthough small at low incidence and flap deflections, becomesmore important at higher values, particularly when separationrelated effects begin to affect the overall flow behavior. Author

N81-13930# Office National d Etudes et de RecherchesAerospatiales. Paris (France)REVIEW OF THEORETICAL AND EXPERIMENTAL RESULTSON THREE DIMENSIONAL TURBULENT WAKES ANDBOUNDARY LAYERSJ. Cousteix. B. Aupoix. and G. Pailhas 1980 54 p refs InFRENCH: ENGLISH summary Report will also be announcedas translation (ESA-TT-678)(ONERA-NT-1980-4: ISSN-0078-3781) Avail: NTISHC A04/MF A01

Various turbulence models were analyzed for boundary layerpredictions: mixing length, transport equations for the componentsof the shear stress. The influence of the shear stress directionwas studied. Various solutions are discussed for taking into accountthe nonalignment between the shear stress and the velocityderivative normal to the wall. Such a nonalignment was alsointroduced in an integral method. The results of an experimentin a wake which is initially strongly dissymmetric and threedimensional are discussed. They were obtained by detailedmeasurements of mean velocities and of the six components ofthe Reynolds stress tensor. Attempts of prediction are dis-cussed. T.M.

N81-13931# ARO. Inc.. Arnold Air Force Station. Tenn.AN EVALUATION OF WIND TUNNEL TEST TECHNIQUESFOR A IRCRAFT NOZZLE A F T E R B O D Y TESTING ATTRANSONIC MACH NUMBERS Final Report. 1 Oct.1 9 7 7 - 1 Jan. 1979T. L Kennedy AEDC Nov. 1980 184 p refs(AD-A091775: AEDC-TR-80-8) Avail: NTISHC A09/MF A01 CSCL 20/4

The results of many experiments to develop and verify windtunnel test techniques for determining engine exhaust effectson aircraft performance at transonic Mach numbers aresummarized. The influence of model support interference, exhaustjet simulation techniques, wind tunnel calibration flow qualityand operating conditions, model geometric effects, and measure-ment techniques in afterbody aerodynamic forces are discussed.Recommendations are given for reducing or eliminating adverseinterference effects on wind tunnel test data. GRA

N81-13932# ARO. Inc.. Arnold Air Force Station. Tenn.EVALUATION OF WIND TUNNEL NOZZLE AFTERBODYTEST TECHNIQUES UTILIZING A MODERN TWIN ENGINEFIGHTER GEOMETRY AT MACH NUMBERS FROM 0.6 TO1.2 Final Report. Oct. 1975 - Sep. 1979Ernest J. Lucas AEDC Oct. 1980 122 p refs(AD-A091545: AEDC-TR-79-63) Avail: NTISHC A06/MF A01 CSCL 01/3

Analyses of surface pressure data from wind tunnel testsconducted in the Propulsion Wind Tunnel (16T) on the 0.1- and0.2-scale models of the YF-17 aircraft and flight tests conductedat the NASA Dryden Flight Research Center with the prototypeYF-17 were conducted to substantiate the effectiveness of thesubscale wind tunnel test techniques currently used at AEDC toprovide data to evaluate throttle-dependent effects. The datawere obtained at Mach numbers 0.6. 0.9. and 1.2 at characteristicReynolds numbers based on fuselage length from 14 million to250 million. The data obtained at Mach numbers 0.6 and 0.9indicate that valid techniques are available to obtain subscalewind tunnel data that are directly applicable to aft-end throttle-dependent flight performance prediction. The wind tunnel plumesimulation techniques, however, do not provide data for directlypredicting the flight vehicle, aft-end. calculated loads at Machnumber 1.2. Additional corrections must be applied to the datato compensate for temperature effects associated with afterburningoperations, such as that encountered at Mach 1.2. GRA

N81-13933# Committee on Public Works and Transportation(U. S. House).AVIATION SAFETY: INTERIOR COMPARTMENT MATERI-ALSWashington GPO 1979 373 p Hearings before the Subcomm.on Oversight and Rev. of the Comm. on Public Works andTransportation, 96th Congr.. 1st Sess.. 25-26 Apr. 1979(GPO 50-388) Avail: Subcommittee on Oversight and Review

Safety efforts are divided into two aspects: accident preventionand accident survivability, or crashworthiness. The hearings focuson the frequent occurence of postcrash fire in survivable aircarrier accidents and on the effect that fire has on the materialswhich surround the passengers in the aircraft cabin.

N81-13934# Committee on Public Works and Transportation(U. S. House).TESTIMONY OF ELWOOD T. DRIVER. VICE CHAIRMAN.NATIONAL TRANSPORTATION SAFETY BOARD, AC-COMPANIED BY GERRIT J. WALKOUT. CHIEF. HUMANFACTORS DIVISION. AND MATTHEW M. MCCORMICK.SENIOR AIR SAFETY INVESTIGATOR. HUMAN FACTORSDIVISIONIn its Aviation Safety: Interior Compartment Mater. 1979 p 4-64

Avail: Subcommittee on Oversight and ReviewThe importance of fuel ignition prevention, and when this

measure fails, the control of fire propagation inside the aircraft.is discussed. Two air carrier accidents investigated by the SafetyBoard are described. It is recommended by the Board that theFAA conduct research in four specific areas affecting the severity

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of injuries of aircraft occupants. These are: (1) containment offlammable fluids, including the fuel. oil. hydraulic fluid, etc.:(2) control of flammable fluids through chemical alteration orthe inerting of fuel systems: (3) the reduction or elimination ofthe toxic effects of burning materials: and (4) improved escapemethodology and passenger education. E.D.K.

N81-13935# Committee on Public Works and Transportation(U. S. House).TESTIMONY OF JAMES J. KRAMER. ASSOCIATE ADMIN-ISTRATOR FOR AERONAUTICS AND SPACE TECHNOL-OGY. NATIONAL AERONAUTICS AND SPACE ADMINIS-TRATION. ACCOMPANIED BY JOHN H. ENDERS. PROJECTMANAGER. AVIATION SAFETY TECHNOLOGY OFFICE.JOHN A. PARKER, CHEMICAL RESEARCH PROJECTSOFFICE. NASA-AMES RESEARCH CENTER. ANDDEMITRIUS A. KOURTIDES. CHEMICAL R E S E A R C HPROJECTS OFFICE. NASA AMES RESEARCH CENTERIn its Aviation Safety: Interior Compartment Mater. 1979p 65-158Avail: Subcommittee on Oversight and Review CSCL 01C

The materials system development program FIREMEN (FireResistant Materials Engineering) is described. The program iscarried out through contracts witrr the major aircraft manufacturerswhereby they are funded to test and evaluate these advancedmaterial systems under the real constraints of state of the artmanufacturing processes, production schedules, costs, weight,and so forth. E.O.K.

N81-13936# Committee on Public Works and Transportation(U. S. House).TESTIMONY OF RICHARD W. TAYLOR. VICE PRESIDENTAND SPECIAL ASSISTANT TO THE PRESIDENT. ANDEUGENE A. BARA. CHIEF ENGINEER. PAYLOAOS SYS-TEMS. BOEING COMMERCIAL AIRPLANE COMPANYIn its Aviation Safety: Interior Compartment Mater. 1979p 159-297Avail: Subcommittee on Oversight and Review

A brief review of the Boeing aircraft interior materials andfire test methods development programs is given. This activityhas gone on for many years and contributed to the AIAcrashworthiness program in 1968. As a result of these activities,the 747 was designed and built using the latest availabletechnology, thereby establishing the requirements for wide bodyjet transports. Boeing's program in interior materials has continuedand the highlights of the last five years are reviewed. E.D.K.

N81-13937# Committee on Public Works and Transportation(U. S. House).TESTIMONY OF A PANEL CONSISTING OF: LLOYD E.FRISBEE. VICE PRESIDENT. ENGINEERING AND OPERA-TIONS. LOCKHEED CALIFORNIA COMPANY; LYLE A.WRIGHT. D I R E C T O R . POWERPLANT ENGINEERING,DOUGLAS AIRCRAFT COMPANY. ACCOMPANIED BYDOCTOR H. C. SCHJELDERUP. CHIEF TECHNOLOGYENGINEER, MATERIALS AND PROCESS ENGINEERING.AND F. E. DUSKIN, SENIOR DESIGN ENGINEER, INTERI-ORS ENGINEERING, DOUGLAS AIRCRAFT COMPANYIn its Aviation and Safety: Interior Compartment Mater. 1979p 298-370Avail: Subcommittee on Oversight and Review

Lockheed has conducted programs to improve aircraft materialflame resistance and develop advanced techniques for firesafetytesting in coordinated programs with other airframe companies,materials suppliers, and NASA. During this time, Lockheed hashad active, continuous liaison with governmental agencies todevelop firesafety testing techniques, study the feasibility andtrade offs for advanced aircraft fire management systems, andseek meaningful and productive areas of research and developmentin aircraft fire safety. Active support and participation was alsomaintained in technical committee work such as ASTM-F7Committee on Aerospace Test Methods to standardize onflammability. smoke, and other combustion byproducts testtechniques and to perform inter-laboratory comparison testingof flammability and smoke emission methods. Improved flam-mability and smoke test techniques have contributed to substantial

improvements in flame resistance of aircraft interior constructionmaterial in all categories and an order of magnitude reductionin smoke emission of materials. In other words, the smoke emissionwas reduced by an order of 10 times in the last few years.

E.D.K.

N81-13938# Naval Weapons Center. China Lake. Calif.AN INVESTIGATION OF SAFETY HAZARDS AND RELIABIL-ITY PROBLEMS IN AERIAL REFUELING STORES FinalReport. Mar. - Jul. 1980Leo D. Budd Aug. 1980 70 p refs(AD-A091788: AD-E900014: NWC-TP-6218) Avail: NTISHC A04/MF A01 CSCL 01/2

An investigation was conducted to identify sources of safetyhazards and reliability problems in model D-704 aerial refuelingstores. A failure modes and effects analysis was performed onthe D-704. Mishap data, safety UR (unsatisfactory report) data.and 3-M (maintenance and material management) data wereanalyzed to identify historical problems. Comparisons of model31-300 failure statistics to model D-704 failure statistics isincluded. GRA

N81-13940# Boeing Military Airplane Development, Seattle,Wash. Aircrew Escape Group.A D V A N C E D EJECTION SEAT FOR HIGH DYNAMICPRESSURE ESCAPE. WIND TUNNEL TEST Final Report.15 Aug. 1979 - 20 May 1980John 0. Bull. David T. Ther. and Roger F. Yurczyk Aug. 1980139 p refs(Contract F3361 5-79-C-3406: AF Proj. 2402)(AD-A091810: AFWAL-TR-80-3084) Avail: NTISHC A07/MF A01 CSCL 01/3

Wind tunnel tests were conducted to evaluate new highdynamic pressure protective devices incorporated into a conven-tional ejection seat. These tests are part of a development program'Advanced Ejection Seat for High Dynamic Pressure Escape'.The objectives of this program are to develop an ejection seatdesign which will provide safe escape during emergencyconditions encountered throughout the performance envelope ofan aircraft with speed capability to 687 KEAS. Preliminary phasesof this program have resulted in selection and definition of awindbiast shield, an aft body drag reduction boom, a horizontalstabilizer and a flow diverter. These devices were incorporatedinto a one-half scale ejection seat/crewmember model andwere tested in the AEDC PWT 16-T transonic tunnel. Aerodynamicdata derived from these tests are being used in six-degree-of-freedom computer simulations for performance assessments ofthe ejection seat configurations. GRA

N81-13941*# Quinby (Gilbert F.). Fort Washington, Pa.AN ASSESSMENT OF GENERAL AVIATION UTILIZATIONOF ADVANCED AVIONICS TECHNOLOGY Final ReportGilbert F. Quinby Dec. 1980 38 p(NASA Order L- 11 593)(NASA-CR-159328) Avail: NTIS HC A03/MF A01 CSCL17G

Needs of the general aviation industry for services and facilitieswhich might be supplied by NASA were examined. In the datacollection phase, twenty-one individuals from nine manufacturingcompanies in general aviation were interviewed against a carefullyprepared meeting format. General aviation avionics manufacturerswere credited with a high degree of technology transfer fromthe forcing industries such as television, automotive, andcomputers and a demonstrated ability to apply advancedtechnology such as large scale integration and microprocessorsto avionics functions in an innovative and cost effective manner.The industry's traditional resistance to any unnecessary regimenta-tion or standardization was confirmed. Industry's self sufficiencyin applying advanced technology to avionics product developmentwas amply demonstrated. NASA research capability could besupportive in areas of basic mechanics of turbulence in weatherand alternative means for its sensing. Author

N81- 13942$ Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Oberpfaffenhofen (West Germany).Abteilung Regelungssysteme.

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THE COLLISION COURSE: CONDITIONS. GUIDANCELAWS AND PROPERTIESWinfried Hofmann Jan. 1980 108 p refs In GERMAN:ENGLISH summary(DFVLR-FB-80-06) Avail: NTIS HC A06/MF A01: DFVLR.Cologne DM 18.40

An evaluation of the influence of distinct missile properties(acceleration phase, lead single constraints and maneuverability)and real world disturbances on the properties and requirementsof collision course guidance is presented. For proportion navigationguidance, comprehensive diagrams are presented to evaluate theterminal miss behavior, the requirements on the missile andon a line of sight angular rate measuring sensor. Missile dynamics,initial alignment errors, target maneuvers and target aspect-anglecaused measurement errors were considered as real worlddisturbances. Author

N81-13944# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany). Inst. fuerFlugmechanik.MIDAIR AND NEAR MIDAIR COLLISIONS ON TWO- ANDTHREE-DIMENSIONAL CURVILINEAR FLIGHT PATHSOtto Weber Mar. 1980 108 p refs In GERMAN: ENGLISHsummary Report will also be announced as translation(ESA-TT-685)(DFVLR-FB-80-13) Avail: NTIS HC A06/MF A01: DFVLR.Cologne DM 21

Collision avoidance by means of the 'see and avoid' concept,advanced secondary radar systems on the ground, and independentelectronic systems onboard is discussed. For two- and three-dimensional stationary turns, basic geometrical and physicalaspects of conflict detection were derived and details given onthe apparent size and motion of the other airplane on thewindshield. For conflict warning by means of electronic systemson the ground or onboard, a linear track model was used. T.M.

N81-13945# Federal Aviation Administration, Atlantic City. N.J.FLIGHT TEST INVESTIGATION OF LORAN-C FOR ENROUTE NAVIGATION IN THE GULF OF MEXICO FinalReportRobert Pursel Sep. 1980 102 p(FAA Proj. 045-390-130)(AD-A091637: FAA-CT-80-18: FAA-RD-80-47) Avail: NTISHC A06/MF A01 CSCL 17/7

Flight tests of a long range navigation (LORAN-C) airbornenavigator were conducted in the Gulf of Mexico oil explorationand production area. Two systems were installed in a CV-580aircraft to examine simultaneously the performance from twodifferent LORAN-C triads. Four separate test loutes were flownover a period of 3 days. These routes covered the eastern, central,and western test areas, and an overland route from Houston.Texas, to Lafayette. Louisiana. An inertial navigation system (INS)was used as a position reference standard. The INS data wereupdated to correct for drift. Accuracy of trie position referencefrom the corrected INS data was - or - 0.3 nautical miles (nmi).The flight test data collected indicated that both the Malone,Raymondville. Jupiter and the Malone. Raymondville. Grangevrlletriads provided en route LORAN-C navigation capability whichmet Federal Aviation Administration (FAA) Advisory CircularAC-90-45A accuracy requirements except when operating nearthe baseline extension of the Malone Grangeville baseline whenusing the Malone. Raymondville. Grangeville triad. GRA

N81-13947# National Technical Information Service. Springfield.Va.MICROWAVE LANDING SYSTEMS. CITATIONS FROM THEENGINEERING INDEX DATA BASE Progress Report.1970 - Jun. 1980Willliam E. Reed Sep. 1980 105 p Supersedes NTIS/PS-79/0778: NTIS/PS-78/0732(PB80-814643: NTIS/PS-79/0778: NTIS/PS-78/0732) Avail:NTIS HC S30.00/MF $30.00 CSCL 17G

The bibliography cites reports from worldwide research onthe planning development, and operation of microwave landingsystems, including feasibility, systems engineering, equipment.

signal propagation, and cost analysis. This updated bibliographycontains 100 abstracts. 11 of which are new entries to theprevious edition. GRA

N81-13948# National Technical Information Service. Springfield.Va.MICROWAVE LANDING SYSTEMS. CITATIONS FROM THENTIS DATA BASE Progress Report. 1964 - Jun. 1980William E. Reed Sep. 1980 205 p Supersedes NTIS/PS-79/0777: NTIS/PS-78/0731(PB80-814635: NTIS/PS-79/0777: NTIS/PS-78/0731) Avail:NTIS HC S30.00/MF $30.00 CSCL 17G

Federally sponsored research on the planning, development,and operation of aircraft microwave landing systems, is presented.Studies include feasibility, systems engineering, equipment, signalpropagation, and cost analysis. This updated bibliography contains181 abstracts, 35 of which are new entries to the previousedition. GRA

N81-13949$ Automation Industries, Inc., Silver Spring. Md.Vitro Labs.WIND SHEAR SYSTEMS INTEGRATION PLAN. VICON(VISUAL CONFIRMATION) RELIABILITY ANALYSIS FinalReportCharles W. Hamby and James R. DeMattio Feb. 1980 74 p(Contract DOT-FA79WA-4279)IPB80-2 18233: VITRO/JOB-03021-03540: FAA-RD-80-61)Avail: NTIS HC A04/MF A01 CSCL 17G

The reliability of a visual confirmation system which visuallyconfirmed that an aircraft awaiting takeoff has been verballycleared for takeoff by the airport controller is examined. It isfound that the predicted availability of the VICON system asinstalled at Bradley International Airport is 99.94% for the sevenmonth test period. It is also found that the number of spareparts to provide a 99% assurance that there will be no degradationof VICON system performance due to a lack of spare parts over6 months is predicted to be sixty-three total spares coveringtwenty-seven different component types. Thirty percent of thespares are required for the controller's operating switches. GRA

N81-13950# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto-brunn (West Germany). Theorgtische Aerodynamik.COMPUTATIONAL AERODYNAMIC DESIGN TOOLS ANDTECHNIQUES USED AT FIGHTER DEVELOPMENTP. Sacher. W. Kraus. and R. Kunz 6 Sep. 1979 54 p refsPresented at Meeting SMP of AGARD., Neubiberg. Germany,3-6 Sep 1979(MBB-FE-122/S/PUB/13) Avail: NTIS HC A04/MF A01

Configuration optimization, component design, and experimen-tal proof in fighter design are summarized. Requirements forsupersonic performance, including supersonic drag reduction andcanard tail design, were reviewed. The main aerodynamic principlesin use throughout the aircraft industry are described. T.M.

N81-13951# Technische Hogeschool. Delft (Netherlands). Dept.of Aerospace Engineering.FUNDAMENTALS OF CONCEPTUAL DESIGN OPTIMIZA-TION OF SUBSONIC TRANSPORT AIRCRAFTE. Torenbeek Aug. 1980 173 p refs(VTH-LR-292) Avail: NTIS HC A04/MF A01

Various merit functions and feasible design program structuresare discussed and program elements common to most designexercises were analyzed. Criteria for optimum cruise conditionsare presented for aircraft with or without Mach number dependentdrag polars and arbitrary propulsion systems. Constrained andunconstrained optima for design cruise speed and altitude, enginethrust, wing loading, aspect ratio and lift coefficient are presentedin the form of generalized analytical expressions. Different criteriawere found when engines were sized for optimum cruising flightor for specified low speed performance. A generalized cruiseperformance analysis is presented for modern turbofan andpropeller aircraft, resulting in new criteria for optimum flightconditions. A detailed account of the aircraft mass breakdownsensitivity to parametric variations, derivations for the payloadfraction, and partial (constrained) and global optima were derived.

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Some opportunities for improvements and extended applicatiito non-conventional and advanced designs are discussed brie

T

ionsiefly.T.M.

N81-13952# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany). Abt.Entwurfsaerodynamik.LAMINAR-AIRFOILS FOR TRANSPORT AIRCRAFTArmin Quasi Mar. 1980 34 p refs In GERMAN: ENGLISHsummary Report will also be announced as translation(ESA-TT-680)(DFVLR-Mitt-80-07; ESA-TT-680) Avail. NTISHC A03/MF A01: DFVLR. Cologne DM 8.30

Wing sections with laminar flow and their effects on fuelconsumption are discussed. It was shown that lammanzation bysection shape is possible at certain Reynolds numbers and atreduced Mach numbers. T.M.

N81-13955# Texas Univ. at Austin. Dept. of AerospaceEngineering and Engineering Mechanics.THE EFFECTS OF WARHEAD-INDUCED DAMAGE ON THEAEROELASTIC CHARACTERISTICS OF LIFTING SUR-FACES. VOLUME 1: AEROELASTIC EFFECTS Final Report.1 Feb. 1979 - 31 Jan. 1980J. H. Chang and R. 0. Stearman Jul. 1980 122 p refs(Grant AF-AFOSR-3569-78; AF Proj. 2301)(AD-A091674; AFOSR-80-1039TR) Avail: NTISHC A06/MF A01 CSCL 01/3

An investigation is being conducted to determine whetherballistic damage can seriously degrade the aeroelastic integrityof lifting surfaces on aircraft. A potential aeroelastic failure modethat was identified in the first year's study has been investigatedhere over a larger range of parameters. This failure mechanismresults from the localized steady drag generated when a liftingsurface encounters damage to its aerodynamic shape. Its modelinghas been extended in this study to swept wing configurationsand to possible multiple and distributed damage sites. In addition,a larger range of single damage site locations has also beenconsidered to assess the possible tradeoffs between the influenceof both structural and aerodynamic damage locations. A checkon the validity of the strip theory aerodynamic modeling employedin this study has also been made by comparing these resultswith those obtained from a lifting surface theory modeling. Finally,an additional failure mechanism is identified that results fromany unsteady but periodic fluctuating aerodynamic drag loadsthat are generated by the damage. A parametric and oscillatoryinstability can be induced by relatively low level drag loads inthis case if they happened to be appropriately tuned to thestructural frequencies of the wing. GRA

N81-13956# Federal Aviation Administration, Oklahoma City,Okla. Standards Development Branch.CURRENT A I R C R A F T SURVEY (APPROACH SPEEDS.GROSS WEIGHTS. AND DIMENSIONS)Frank Parr Jul. 1980 36 p(Proj. AFS-560-79-17)(PB80-225691: FAA-AFO-500-20) Avail: NTISHC A03/MF A01 CSCL01B

A survey of current aircraft was conducted to determinethe effect of a revision to FAR 97.3. The revision deleted theuse of gross weight in categorization of aircraft for instrumentapproach minimums. Of 237 aircraft types and models of 22nations surveyed. 180 were not affected by the rule change. Ofthe affected aircraft, 31 changed from Category D to C, onefrom D to B, one from D to A. 17 to C to B, three from C toA. and four from B to A. Ten aircraft types have series whichfall into two categories. GRA

N81-13957*# New Mexico Univ.. Albuquerque. TechnologyApplication Center.TECHNOLOGICAL FORECASTING-AIR CRAFT DESIGN.CITATIONS FROM THE INTERNATIONAL AEROSPACEABSTRACTS DATA BASE Progress Report. 1974 - Aug. 1980Gerald F. Zollars and Mary K. Gallagher Sep. 1980 45 pSupersedes NTIS/PS-79/1017 Sponsored in part by NASAand NTIS

(NASA-CR-163833: PB80-815970. NTIS/PS-79/1017) Avail:NTIS HC S30.00/MF $30.00 CSCL01C

Technological forecasts of aircraft design are discussed inapproximately 162 citations. Forecasts dealing with the configura-tion of both civil and military aircraft are included. Specific topicsstressed are fuel consumption, avionics, and cost and noisereduction. GRA

N81-13958*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.

EVALUATION OF A COMPUTER-GENERATED PERSPEC-TIVE TUNNEL DISPLAY FOR FLIGHT PATH FOLLOWINGArthur J. Grunwald. James B. Robertson, and Jack J. HatfieldDec. 1980 100 p refs(NASA-TP-1736: 1-13253) Avail: NTIS HC A06/MF A01CSCL 01 D

The display was evaluated by monitoring pilot performancein a fixed base simulator with the vehicle dynamics of a CH-47tandem rotor helicopter. Superposition of the predicted futurevehicle position on the tunnel image was also investigated todetermine whether, and to what extent, it contributes to bettersystem performance (the best predicted future vehicle positionwas sought). Three types of simulator experiments wereconducted: following a desired trajectory in the presence ofdisturbances: entering the trajectory from a random position,outside the trajectory: detecting and correcting failures inautomatic flight. The tunnel display with superimposed predictor/director symbols was shown to be a very successful combination,which outperformed the other two displays in all three experiments.A prediction time of 4 to 7 sec. was found to optimize trajectorytracking for the given vehicle dynamics and flight condition.Pilot acceptance of the tunnel plus predictor/director displaywas found to be favorable and the time the pilot needed forfamiliarization with the display was found to be relatively short.

Author

N81-13959*# National Aeronautics and Space Administration.Langley Research Center, Hampton. VaDEVELOPMENT OF A COMPUTER PROGRAM DATA BASEOF A NAVIGATION AID ENVIRONMENT FOR SIMULATEDIFR FLIGHT AND LANDING STUDIESHugh P. Bergeron. Alix T. Haynie (Georgia Inst. of Tech.), andJames B. McDede (Embry-Riddle Aeronautical Inst.) Nov. 198035 p refs(NASA-TM-80064) Avail: NTIS HC A03/MF A01 CSCL17G

A general aviation single pilot instrument flight rule simula-tion capability was developed. Problems experienced by singlepilots flying in IFR conditions were investigated. The simulationrequired a three dimensional spatial navaid environment of aflight navigational area. A computer simulation of all thenavigational aids plus 12 selected airports located in theWashington/Norfolk area was developed. All programmedlocations in the list were referenced to a Cartesian coordinatesystem with the origin located at a specified airport's referencepoint. All navigational aids with their associated frequencies, callletters, locations, and orientations plus runways and true headingsare included in the data base. The simulation included a TVdisplayed out-the-window visual scene of country and suburbanterrain and a scaled model runway complex. Any of theprogrammed runways, with all its associated navaids, can bereferenced to a runway on the airport in this visual scene. Thisallows a simulation of a full mission scenario including breakoutand landing. R.C.T.

N81-13960# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany). AbteilungFlugsimulation.EQUIPMENT FOR TESTING AND MEASURING A 'HELMETMOUNTED SIGHT AND DISPLAY1 SYSTEM WITH ACOUPLED MOVABLE TELEVISION C A M E R A IN THEFLIGHT-SIMULATOR FOR RESEARCH OF THE DFVLRR. Dierke. Friedrich Erdmann. E. Biertuempel. R. Ehlers. and H.Loehr Jan. 1980 81 p refs In GERMAN: ENGLISH summaryReport will also be announced as translation (ESA-TT-675)(DFVLR-Mitt-80-04) Avail: NTIS HC A05/MF A01

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Equipment for testing a helmet mounted sight and displaysystem (HMS/D) in a flight simulator is described. After definingthe values to be measured and the corresponding reference values,the software and hardware of the testing equipment is described,as well as the control program of the equipment and the methodsof data recording. Special aspects of the mathematical backgroundand measurement of static errors of a HMS/D System (Honeywell)are given in the appendices. E.D.K.

N81-13963*# Teledyne Continental Motors. Mobile. Ala. AircraftProducts Div.ADVANCED TECHNOLOGY SPARK-IGNITION AIRCRAFTPISTON ENGINE DESIGN STUDY Final ReportKenneth J. Stuckas Nov. 1980 127 p refs x(Contract NAS3-21272)(NASA-CR-165162) Avail: NTIS HC A07/MF A01 CSCL21G

The advanced technology, spark ignition, aircraft piston enginedesign study was conducted to determine the improvements thatcould be made by taking advantage of technology that couldreasonably be expected to be made available for an engineintended for production by January 1, 1990. Two engines wereproposed to account for levels of technology considered to bemoderate risk and high risk. The moderate risk technology engineis a homogeneous charge engine operating on avgas and offersa 40% improvement in transportation efficiency over presentdesigns. The high risk technology engine, with a stratified chargecombustion system using kerosene-based jet fuel, projects a 65%improvement in transportation efficiency. Technology enablementprogram plans are proposed herein to set a timetable for thesuccessful integration of each item of required advancedtechnology into the engine design. , Author

N81-13964| Rolls-Royce Ltd.. Derby (England).THE FUTURE OF CIVIL TURBO-FAN ENGINESA. G. Newton and J. F. Coplin 1980 41 p(PNR-90034) Avail: NTIS HC A03/MF A01

The scarcity of fuel and rapidly increasing fuel prices meansthat there will be ever increasing pressure to reduce the fuelconsumption of commercial aeroengines. The present generationof large fan engines has consolidated significant improvementsin this respect compared with the engines it replaced. The fuelconsumption of this class of engines can be greatly reduced (byamount 12-15 percent) by adopting a derivative approach and.in the longer term, by a further 10 percent by more radicalchanges. The methods by which the current performance wasachieved are described. Author

N81-13966# School of Aerospace Medicine. Brooks AFB, Tex.Aerospace Medical Div.ORGANIC COMPOUNDS IN THE EXHAUST OF A J8S-STURBINE ENGINE Interim Report. Jan. - Sep. 1978James P. Conkle. William W. Lackey. Charles L Martin, andAndrew Richardson, III Sep. 1980 35 p refs(AF Proj. 7930)(AD-A091712: SAM-TR-80-29) Avail: NTISHC A03/MF A01 CSCL 21/2

Information related to exhaust hydrocarbons associated witha J85-5 turbine engine is presented. A comparison of two samplingtechniques (cryogenic trapping and sorption tube) is discussed.The collected samples were analyzed by coupled gas chromato-graph-mass spectrometer-data system. The number of com-pounds identified in the samples was 231. with equivalent resultsfrom the two sampling techniques. Less than half of thecompounds identified were aromatic and oxygenated species.

GRA

N81-13968*# National Aeronautics and Space Administration.Langley Research Center. Hampton, Va.ECONOMIC EVALUATION OF FLYING-QUALITIES DESIGNCRITERIA FOR A TRANSPORT CONFIGURED WITHRELAXED STATIC STABILITYSteven M. Sliwa Dec. 1980 30 p refs(NASA-TP-1760: L-13944) Avail: NTIS HC A03/MF A01CSCL 01C

Direct constrained parameter optimization was used tooptimally size a medium range transport for minimum directoperating cost. Several stability and control constraints were variedto study the sensitivity of the configuration to specifying theunaugmented flying qualities of transports designed to takemaximum advantage of relaxed static stability augmentationsystems. Additionally, a number of handling qualities related designconstants were studied with respect to their impact on thedesign. Author

N81-13969*# Calspan Advanced Technology Center. Buffalo,N.Y.LANDING FLYING QUALITIES EVALUATION CRITERIA FORAUGMENTED AIRCRAFT Final ReportRobert C. Radford. Roger Smith, and Randall Bailey Jun. 198099 p refs(Contract NAS4-2534)(NASA-CR-163097: CALSPAN-6339-F-3) Avail: NTISHC A05/MF A01 CSCL 01C

The criteria evaluated were: Calspan Neal-Smith: Onstott(Northrop Time Domain); McDonnell-Douglas Equivalent SystemApproach: R. H. Smith Criterion. Each criterion was applied tothe same set of longitudinal approach and landing flying qualitiesdata. A revised version of the Neal-Smith criterion which isapplicable to the landing task was developed and tested againstother landing flying qualities data. Results indicated that boththe revised Neal-Smith criterion and the Equivalent SystemApproach are good discriminators of pitch landing flying qualities:Neal-Smith has particular merit as a design guide, while theEquivalent System Approach is well suited for development ofappropriate military specification requirements applicable to highlyaugmented aircraft. Author

N81-13970# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst.fuer Dynamik der Flugsysteme.APPLICATION OF VECTOR PERFORMANCE OPTIMIZA-TION TO A ROBUST CONTROL LOOP DESIGN FOR AFIGHTER AIRCRAFTGerhard Kreisselmeier and Reinhold Steinhauser Apr. 198070 p refs In GERMAN: ENGLISH summary(DFVLR-FB-80-14) Avail: NTIS HC A05/MF A01: DFVLR.Cologne DM 13.20

For a McDonnell-Douglas F-4C aircraft a robust, fixed gaincontroller is designed, which provides satisfying handling qualitiesof the longitudinal motion of the aircraft over the complete flightrange without gain scheduling. Robustness is achieved in thesense of covering large parameter variations and providing goodgain and phase margins. Only low control rates and low feedbackgains are involved. The results are obtained by application of aperformance vector optimization design method which permits agreat many different design objectives simultaneously and in ahighly systematic fashion. Two different designs are presentedplacing emphasis on pitch rate control and normal accelerationcontrol. E.D.K.

N81-13971# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany). Abt.Flaechenflugzeuge.SYSTEM IDENTIFICATION OF THE LONGITUDINALMOTION OF THE DFVLR HFB 320 RESEARCH AIRCRAFTWITH PARTICULAR CONSIDERATION OF CONTROLSURFACE EFFECTIVENESSOhad Rix Jul. 1979 58 p ref In GERMAN: ENGLISH summaryReport will also be announced as translation (ESA-TT-666)(DFVLR-Min-79-16) Avail: NTIS HCA04/MFA01

The identification of the longitudinal motion of the DFVLRHFB 320 research aircraft using a maximum likelihood methodis described. The main emphasis is on the identification of controlsurface effectiveness of separately or simultaneously deflectedDLC flaps and spoilers. The flight test technique and the influenceof different model approaches on the results are discussed.

E.D.K

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N81-13972# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto-brunn (West Germany). Airplane Div.ACTIVE FLUTTER SUPPRESSION ON AN F-4F AIRCRAFTWITH EXTERNAL STORES USING ALREADY EXISTINGCONTROL SURFACES0. Sensburg. H. Hoenlinger. and T. E. Moll (AFFDU 25 Mar.1980 9 p refs Presented at AIAA 21st Struct.. Struct. Dyn.and Mater. Conf, Seattle. 12-14 May. 1980(MBB-FE-17/S/PUB/24) Avail: NTIS HC A02/MF A01

The flutter suppression system was flight tested using classicalflight flutter tests, open loop tests, and closed loop tests. Thecontrol law was found by applying optimal control theory thusminimizing the control surface motion due to disturbances andproviding the required stability margins. The selection of thewing mounted store configuration is described. T.M.

N81-13973# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto-brunn (West Germany). Airplane Div.ACTIVE CONTROL OF AN EXPLOSIVE WING-STOREFLUTTER CASEH. Hoenlinger. 0. Sensburg. M. Kuehn, and H. Goedel 8 Apr.1980 9 p refs Presented at 50th Meeting Struct, and Mater.Panel of AGARD. Athens. 13-18 Apr. 1980(MBB-FE-17/S/PUB/25) Avail: NTIS HC A02/MF A01

Control laws were calculated, using optimal control theory,to suppress an explosive wing store flutter case on a YF-17 dynamically scaled model. The trailing edge flap was usedfor flutter suppression because usually hydraulically driven aileronsare available in modern fighters. The design aim of 15 timesthe flutter dynamic pressure could be demonstrated during thewind tunnel test. It should be emphasized that no changes tothe analytically developed control law were necessary in thetest which proves that theory has well advanced during the lastyears. E.D.K.

N81-13974$ Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto-brunn (West Germany). Airplane Div.EFFECTS OF NONLINEARITIES ON WING STORE FLUT-TERG. DeFerrari. L Chesta. 0. Sensburg. and A. Lotze 9 Apr.1980 16 p refs Presented at 50th Meeting Struct, and Mater.Panel of AGARD.. Athens. 13-18 Apr.. 1980 Prepared jointlywith Agritalia. Turin(MBB-FE-17/S/PUB/27) Avail: NTIS HC A02/MF A01

The effects of structural nonlinearities, in particular frictionand backlash, on the dynamic behavior of airplanes can bevery important for flutter. Larger nonlinearities do exist onsweepable wing airplanes with sweepable wing mounted storesbecause a considerable amount of joints (with possible play)and bearings (with play and friction) is necessary but the problemis also present for fired wing airplanes. A major problem is theinterpretation of linear ground resonance and flight flutter testsand their comparison with analytical predictions. Findings fromground resonance tests and flight flutter tests are presentedand an explanation for these test results is given. Calculationswith linear assumptions (parameter variations) were made andthe method of harmonic balance for finding these parameterswas applied. It is shown certain levels of excitation must bereached in order to make flight flutter tests reliable for establishingflutter clearance speeds. Author

N81-13975# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Brunswick (West Germany). AbteilungFlaechenflugzeuge.THEORETICAL INVESTIGATION OF THE INFLUENCE OFSPOILER DYNAMICS ON THE HANDLING QUALITIES OFAN AIRCRAFT WITH DIRECT LIFT CONTROLDieter Schafranek Nov. 1979 72 p refs In GERMAN: ENGLISHsummary Report will also be announced as translation(ESA-TT-68D(DFVLR-FB-80-07) Avail: NTIS HC A04/MF A01: DFVLR.Cologne DM 14.70

Parameters describing the pilots workload during pitch trackingand flight path tracking tasks on a transport aircraft equippedwith spoiler direct lift control (DLC) were determined. The

determined parameters are the necessary phase compensationand gain adaption which the pilot must perform and also theclosed loop resonance. The influence of DLC gain factor, spoileractuator rate and spoiler deflection wash-out time constant onpilot workload, is presented. Simulated time histories of pitchrate and normal acceleration response due to step type controlinputs show the corresponding reactions of the various DLCconfigurations which are essential for pitch control and flightpath control. Author

N81-139770 Calspan Corp., Buffalo. N. Y.FURTHER INVESTIGATIONS OF ADAPTIVE-WALL WINDTUNNELS Final Report. Aug. 1978 - Dec. 1979J. C. Erickson. Jr.. C. E. Wittliff. and D. C. Daughtery Oct.1980 72 p refs(Contract F40600-78-C-0003)(AD-A091774: CALSPAN-6374-A-1: AEDC-TR-80-34) Avail:NTIS HC A04/MF A01 CSCL 20/4

The objective of this investigation was to continue theassessment of the Calspan perforated-wall, segmented-plenumadaptive-wall wind tunnel for flows in which the tunnel wallsare supercritical. An important aspect of the investigation wasthe development of a static pipe measuring technique fordetermining the normal velocity distributions. This techniquewas developed to overcome the limitations on the number offlow angle probe measurements that could be made in the Calspantunnel The flow about a static pipe in the presence of model/wallinduced disturbances was analyzed within the framework ofslender body theory to give the relationship between differentialpressure measurements across the pipe and the steam wisederivative of the normal velocity at the pipe centerline. GRA

N81-14004# Rolls-Royce Ltd.. Derby (England). Plastics andComposite Materials Lab.A RESIN INJECTION TECHNIQUE FOR THE FABRICATIONOF AERO ENGINE COMPOSITE COMPONENTSW. R. Jones and J. W. Johnson 1980 10 p(PNR-90024) Avail: NTIS HC A02/MF A01

A method for the manufacture of high quality compositeaero engine components, free from voids and having a highdegree of dimensional reproducibility is described. A porous fiberpreform held in the component shape by the use of a thermoplasticbinder is employed. The preform is then infiltrated with epoxyresin in a closed die using a vacuum assisted high pressureinjection method. It is possible to include inserts or third dimensionreinforcement in components, and reference is made to theproduction of a carbon fiber fan blade and a nose spinner. S.F.

N81-14O06# Messerschmitt-Boelkow-Blohm G.m.b.H.. Otto-brunn (West Germany). Aircraft Div.CONSTANT-AMPLITUDE AND FLIGHT-BY FLIGHT TESTSON CERP SPECIMENSF. J. Arendts. K. 0. Sippel. and D. Weisgerber 9 Apr. 198013 p refs Presented at 50th Meeting Struct, and Mater. Panelof AGARD, Athens, 13-18 Apr., 1980 Supported by FRG Min.of Defense(MBB-FE-2/S/PUB-26) Avail: NTIS HC A02/MF 01

Constant-amplitude and flight-by-flight tests with five differentload spectra were done with unnotched carbon fiber reinforcedpoints specimens. Also the influence of overloads was investigated.The test results were compared with fatigue life predictions basedon 'Miner's Rule' applied for different conditions. The resultsshow that overloads in all cases cause a significant reduction ofthe fatigue life. It turned out that fatigue life estimations basedon 'Miner's Rule' are on the unsafe side in some cases bymore than a factor 10. getting a big scatter among the casesinvestigated. Author

N81-14061# Systems Research Labs.. Inc.. Dayton. Ohio.Research Applications Div.THE STRESS BEHAVIOR OF THREE ADVANCED NICKELBASE SUPERALLOYS DURING HIGH TEMPERATURE LOWCYCLE FATIGUE Technical Report. Jan. 1977 - Aug. 1978

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Henry L. Bernstein Jun. 1980 243 p refs(Contract F33615-76-C-5191: AF Proj. 7351)(AD-A091694; SRL-9799: AFWAL-TR-80-4075) Avail: NTISHC A11/MF A01 CSCL 11/6

This report is a compilation of data on stress behavior as afunction of cycles obtained during high temperature, low cyclefatigue tests on three advanced Ni-base superalloys--Rene 95.AF-115. and AF2-1DA. The data are presented in both tabularand graphical formats. The materials studied are those used forjet engine turbine disks, and the fatigue tests were conductedat their operating temperatures. The purpose of this report is tomake the test data available to the technical community. Nodiscussion is presented on an analysis or an understanding ofthe data, although some observations are included. GRA

N81-14O64# Massachusetts Inst. of Tech.. Cambridge. Lab.for Manufacturing and Productivity.PREVENTION OF SPUNE WEAR BY SOFT METALLICCOATINGS Final Report. 1 Jan. 1977 - 30 Jun. 1979Nannaji Saka. Hyo Choi Sin. and Nam P. Suh Jul. 1980 71 prefs(Contract N00014-76-C-0068)(ADA091861: MIT/LMP/TRB-80-2) Avail: NTISHC A04/MF A01 CSCL 01/3

The purpose of this cooperative program between MIT. NavalAir Development Center (NAOC) and Foxboro-Analytical is tostudy the mechanism of wear and increase the wear resistanceof aircraft splines. In addition to testing a much larger numberof splines under a variety of conditions than has been done sofar. optical microscopy, scanning electron microscopy andferrography have been extensively used to identify the wearmechanism. Test specimens of aircraft splines were coated withAu. Ni. Ag and Cd with various thicknesses (0.1 - 10 micronm) and tested in the SwRI spline wear tester with and withoutgrease. The gold coated splines exhibited induction periods of250 hours, which is four times that exhibited by the uncoatedsplines. Ni. Ag and Cd failed to increase the induction period.Unluhncated splines wore exactly at the same rate as thepost-induction wear rates of the grease lubricated splines. Opticaland scanning electron microscopy results indicate that the modeof wear is by subsurface deformation, crack nucleation and growthprocesses (i.e.. by the delamination mechanism) both in theinduction and the post-induction periods. Analysis of the splinesby the energy dispersive X-ray analysis showed that the metalliccoatings did not react with grease. This and other evidenceindicates that the costing/substrate bond strength is an importantfactor in the wear of splines. Methods for improving the bondstrength and reducing the cost of the coatings are suggested.

GRA

N81-14077* National Aeronautics and Space Administration.Lyndon B. Johnson Space Center, Houston. Tex.SURFACE FINISHING PatentJack A. Kinzler. James T. Hefferman. Leroy G. Fehrenkamp. andWilliam S. Lee. inventors (to NASA) Issued 30 Sep. 19808 p Filed 25 Jan. 1979 Supersedes N79-21183 (17-12.p 1540) Continuation of abandoned US Patent Appl. SN-785279.filed 6 Apr. 1977 which is a division of US Patent Appl.SN-568541. US Patent-4. 032. 089. filed 16 Apr. 1975(NASA-Case-MSC-12631-3: US-Patent-4.225.372:US-Patent-Appl-SN-006952: US-Patent-Class-156-154:US-Patent-Class-156-160: US-Patent-Class-156-163:US-Patent-Class-156:212: US-Patent-Class-156-267:US-Patent-Class-156-295: US-Patent-Class-156-323:US-Paient-Class-156-331: US-Patent-Appl-SN-785279:US-Patent-Appl-SN-568541: US-Patent-4.032.089) Avail: USPatent and Trademark Office CSCL 11A

A surface of an article adapted for relative motion with afluid environment is finished by coating the surface with a fluidadhesive, covering the adhesive with a sheet of flexible filmmaterial under tension on the film material whereby the tensionedfilm material is bonded to the surface by the adhesive.

Official Gazette of the U.S. Patent and Trademark Office

N81-14082*# General Electric Co.. Philadelphia. Pa. AdvancedEnergy Programs Dept.IMPROVED CERAMIC HEAT EXCHANGER MATERIALSFinal ReportHarry W. Rauch Dec. 1980 39 p refs(Contracts NAS3-19698 EC-77-A-31-101 1:DE-AI01-77CS-51040)(NASA-CR-159678: DOE/NASA/9698-2) Avail: NTISHC A03/MF A01 CSCL 07C

The development and evaluation .of materials for potentialapplication as heat exchanger structures in automotive gas turbineengines is discussed. Test specimens in the form of smallmonolithic bars were evaluated for thermal expansion anddimensional stability before and after exposure to sea salt andsulfuric acid, followed by short and long term cycling attemperatures up to 1200 C. The material finally selected. GE-7808.consists of the oxides. 2rO2-MgO-AI2O3-S102. and is describedgenerically as ZrMAS. The original version was based on acommercially available cordierite (MAS) frit. However, a clay/talcmixture was demonstrated to be a satisfactory very low costsource of the cordierite (MAS) phase. Several full size honeycombregenerator cores, about 10.2 cm thick and 55 cm diameterwere fabricated from both the frit and mineral versions of GE-7808.The honeycomb cells in these cores had rectangular dimensionsof about 0.5 mm x 2.5 mm and a wall thickness of approximately0.2 mm. The test data show that GE-7808 is significantly morestable at 1100 C in the presence of sodium than the aluminosilicatereference materials. In addition, thermal exposure up to 1100 C,with and without sodium present, results in essentially no changein thermal expansion of GE-7808. M.G.

N81-14084# Naval Weapons Center. China Lake. Calif.VANADIUM TRINEODECANOATE PROMOTER FORFIBERGLASS-POLYESTER SOIL SURFACINGS Final Report.Apr. 1979 - Mar. 1980Alan L. Woodman. Ronald A. Henry, Arnold Adicoff. and DwightA. Fine Jun. 1980 30 p refs(AD-A091785 : AD-E900008: NWC-TP-6184) Avail: NTISHC A03/MF A01 CSCL 11/2

A Marine Corps chemical formulation developed for theconstruction of fiberglass-reinforced plastic surfaces for soilsconsists of a polyester resin, cumene hydroperoxide catalyst anda promoter solution containing a vanadium salt and N.N-dimethyl-p-toluidine. A new. relatively simple method for preparing thevanadium trineodecanoate (VND) solution has been devised toreplace the previously used commercial salt solution which isno longer being manufactured. This preparation is now ready tobe scaled-up to pilot plant size. Reactivity and accelerated agingstudies indicate that the VND solution functions at least as wellas the commercial salt. Laminates made under either dry orwet conditions with the VND displayed significantly higherflexural strengths than those made with the commercialmaterial. GRA

N81-14182| Transportation Research Board. Washington. D.C.SEALING JOINTS AND CRACKS. THIN RESURFACING.AND LOCATING VOIDS UNDER CONCRETE SLABSWouter Gulden. Gordon K. Ray. I. Minkarah, J. P. Cook, and J.B. Thornton 1980 38 p refs(PB80-215635: TRB/TRR-752: ISBN-0-309-03062-5:LC-80-23303) Avail: NTIS HC A03/MF A01 CSCL 13B

The six papers in this report deal with the following areas:effect of defective joint seals on pavement performance: pavementdesign features and their effect on joint seal performance:pavement restoration measures to precede joint resealing: andconditions and operations for joint and crack resealing of airfieldpavement. The use of a very thin overlay to reestablish the skidresistance of a concrete pavement and applicability of radarsubsurface profiling in estimating sidewalk undermining are alsodiscussed. GRA

N81-14195# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Oberpfaffenhofen (West Germany). Inst.fuer Hochfrequenztechnik.

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VOLUMETRIC PATTERN PREDICTION OF ANTENNAS ONAIRCRAFT USING THE GEOMETRICAL THEORY OFDIFFRACTION Ph.D. Thesis - Kaiserslautern Univ.Thomas Jank Nov. 1979 178 p refs In GERMAN: ENGLISHsummary Report will also be announced as translation(ESA-TT-677)(DFVLR-FB-80-01: TT-677) Avail: NTIS HC A09/MF A01

The patterns of small dipoles or slot antennas mounted onthe fuselage of an aircraft are computed in the high frequencycase. For the computation of the field the geometrical theory ofdiffraction is used. A very versatile and realistic mathematicalaircraft mode is developed. The construction of all rays whichcontribute considerably to the total field is a complicated numericalproblem. Via the solution of this ray tracing problem it is possibleto obtain arbitrary pattern cuts. Author

N81-14265*# National Aeronautics and Space Administration.Ames Research Center. Moffett Field. Calif.EXPERIMENTAL STUDY OF SUPERSONIC VISCOUSLEESIDE FLOW OVER A SLENDER DELTA WINGJoachim Szodruch Dec. 1980 62 p refs(NASA-TM-81248: A-8408) Avail: NTIS HC A04/MF A01CSCL 200

An investigation was conducted to study in detail the vorticalflow over the leeward side of a 70 deg swept delta wing havingsubsonic and supersonic leading edges. Two types of flow wereencountered and studied, namely leading edge separation andseparation with a shock. Especially for the latter type. Reynoldsnumber plays an important role and unexpected strong stream-wise vortices were observed. An optical method is described toobtain a first aproximation of shear stress values in the streamwisedirection across the wing span. Author

N81-14275# ARO. Inc.. Arnold Air Force Station. Tenn.LASER-RAMAN/RAYLEIGH FLOW DIAGNOSTIC TECH-NIQUES APPLIED TO SUBSONIC FLOW Final Report.13 Apr. 1977 - 14 Mar. 1978W. D. Williams. D. W. Sinclair, and L L Price AEDC Oct.1980 57 p refs Sponsored by Air Force(AD-A091695: AEDC-TR-80-20) Avail: NTISHC A04/MF A01 CSCL 20/4

The feasibility of performing laser-Raman/Rayleigh scatteringmeasurements in subsonic flows was demonstrated in the 6 in.Acoustic Research Tunnel (ARTI of the Propulsion Wind Tunnelfacility at AEDC. The ART is an open-circuit, atmospheric inbleedtunnel that operates on the Plenum Evacuation System of the16 ft transonic Propulsion Wind Tunnel (16T). Laser-Raman/Rayleigh scattering techniques were used to measure air numberdensity, H20 number density, and static temperature and todetect the onset of water vapor condensation. Measurementswere made near the tunnel axial centerline over the Mach numberrange from 0.10 to 0.80. Measurements were also made in theturbulent boundary layer on the wall of the test section at Machnumbers 0.50 to 0.80. GRA

N81-14276/JI Air Force Wright Aeronautical Labs., Wright-Patterson AFB, Ohio.EFFECTS OF DOWNSTREAM DISTANCE ON TURBULENCEDECAY FOR THE COMPRESSOR RESEARCH FACILITY LOWCONDITIONING SYSTEM Final Report. 1 Feb. 1978 - 1 Jul.1979Douglas C. Rabe Mar. 1980 72 p refs(AF Pro). 3066)(AD-A091543: AFWAL-TR-80-2023) Avail: NTISHC A04/MF A01 CSCL 14/2

The turbulence decay of the 304.8 cm (120 in) diameterflow conditioning system for the Air Force Aero PropulsionLaboratory's Compressor Research Facility was investigated in a25.4 cm (10 in) diameter channel to predict turbulence levelsthat can be expected at the entrance to compressors beingtested in the facility. Results of this experimentation show thatthe flow conditioning system will meet the design goal of reducingthe expected imcoming turbulence level of 30-40% to less than1% at the entrance to a test compressor. Further, the turbulence

decay associated with the full-flow conditioning system and itsindividual components possesses initial period of decay character-istics throughout the 600 cm decay length investigated. It isconcluded that these decay characteristics are due to the largescale of turbulence incoming and exiting the flow conditioningsystem of the Compressor Research Facility. GRA

N81-14289# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt, Goettingen (West Germany). Inst. fuerExperimentelle Stroemungsmechanik.A COMPUTER-BASED LASER DOPPLER VELOCIMETERJens-Carsten Petersen Jun. 1979 64 p refs In GERMAN:ENGLISH summary(DFVLR-Mitt-79-14) Avail: NTIS HC A04/MF A01: DFVLR.Cologne DM 11.50

A Laser-Doppler-Velocimeter is described which is speciallydesigned for windtunnel applications. Facing other Velocimetersthe data analysis is here performed digitally by use of acomputer. The control of the testing procedure is also done bythe computer, while a remote control is installed betweencomputer and positioning control for the optical part of theVelocimeter. built up on two three-axis-travers mechanisms. Thisremote control generates or improves all signals necessary forcontrol procedures. In addition to the description of thesystem's functions, necessary and desirable improvements arebriefly discussed. Author

N81-14292# Institut Franco-Allemand de Recherches, St. Louis(France).THE DALEMBERTOMETERP. Smigieiski and P. G. Sava 20 Nov. 1979 9 p refs Presentedat 2nd European Congr. on Opt. Appl. to Metrology (OPIEM79). Strasburg. Nov. 1979(ISL-CO-220/79) Avail: NTIS HC A02/MF A01

A new device is presented utilizing a He-Ne 5 mW laser asa light source, and including a Mach-Zehnder interferometercoupled with schlieren systems with defocalized phase platespermitting the measurement of the dalembertian of the opticalpath along a trajectory of the laser beam in a transparent medium.This device which required a long development, as much opticallyas electronically, is used for the study of noise sources in theair jets. The particularities of the system are described and itsperformances are illustrated by applications in aerodynamics.

Author

N81-14300# Institut Franco-Allemand de Recherches. St. Louis(France).CONTROLS OF AERONAUTICAL STRUCTURES UNDERFATIGUE TESTING BY HOLOGRAPHIC PULSED LASERSINTERFEROMETRYH. Fagot. F. Albe. P. Smigieiski. A. Stimpfling. and J. L. Arnaud(SNIAS) 20 Nov. 1979 11 p refs Presented at 2nd EuropeanCongr. on Opt. Appl. to Metrology (OPIEM 79), Strasburg. Nov.1979 Sponsored in part by Direction des Recherches, Etudeset Techniques(ISL-CO-218/79) Avail: NTIS HC A02/MF A01

A compact and mobile holographic camera is described whichis capable of recording holograms by double exposure. The timelapse between the 2 laser impulses (duration 20 ns, energy100 mj approx.) is adjustable from 0.1 micron to infinity. Thesuccessful 'in situ' experimentation of this device took placewhile bars of aeronautical structures were being tested forfatigue (periodical tensile stress). The holograms were recordedwithout interrupting the fatigue testings which lasted severalhours. The testbars being used were chosen because theircharacteristics demonstrate problems typically met in aeronau-tics. A.R.H.

N81-14318* National Aeronautics and Space Administration.Pasadena Office. Calif.POWER CONTROL FOR HOT GAS ENGINES PatentWilliam F. MacGlashan. inventor (to NASA) (JPL) Issued 21 Oct.1980 10 p Filed 19 May 1978 Supersedes N78-25430(16 - 16, p 2122) Sponsored by NASA

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(NASA-Case-NPO-14220-1: US-Patenl-4.228.656:US-Patent-Appl-SN-907421: US-Patent-Class-60-518:US-Patent-Class-74-417) Avail: US Patent and TrademarkOffice CSCL 131

A hot gas engine in which the expander piston of the engineis connected to an expander crankshaft. A displacer piston ofthe engine is connected to a separate displacer crankshaft whichmay or may not be coaxial with the expander crankshaft. Aphase angle control mechanism used as a power control forchanging the phase angle between the expander and displacercrankshaft is located between the two crankshafts. The phaseangle control mechanism comprises a differential type mechanismcomprised of a pair of gears, as for example, bevel gears, oneof which is connected to one end of the expander crankshaftand the other of which is connected to the opposite end of thedisplacer crankshaft. A mating bevel gear is disposed in meshingengagement with the first two level gears to provide a phaseangle control between the two crankshafts. Other forms ofdifferential mechanisms may be used including conventional spurgears connected in a differential type arrangement.

Official Gazette of the U.S. Patent and Trademark Office

COMPRESSOR CONFIGURATION AND DESIGN OPTIMIZA-TION FOR THE HIGH RELIABILITY GAS TURBINE FinalReportDiana L. Day and Fred H. Boenig Apr. 1980 54 p Preparedin cooperation with Pratt and Whitney Aircraft. West Palm Beach.Fla.(Contract DE-AC03-79ET-15425)(DOE/ET-15425/T1: GTR-2136) Avail: NTISHC A04/MF A01

The compressor and diffuser preliminary designs were complet-ed to define size and performance characteristics. The compressorhas 9 stages and a predicted adiabatic efficiency of 8835%.The diffuser selected is a conventional straight wall configura-tion with an equivalent conical angle of 8 degrees. An alternatediffuser configuration was recommended because of its excellentperformance potential in high Mach number applications. TheHTF compressor configuration appears to offer equivalent COEand reliability as compared to the Baseline Reliable Engineconfiguration, but at more conservative aerodynamic loadinglevels. J.M.S.

N81-14324# Lord Kinematics. Erie. Pa.SERVICE LIFE DETERMINATION FOR THE UH-60-A(UTTAS) HELICOPTER ELASTOMERIC BEARINGS FinalReport. Aug. 1978 - Apr. 1980Ernest P. Gaudette Apr. 1980 86 p(Contract DAAG46-78-C-0030)(AD-A091756; APE-79-021: USAAVRADCOM-TR-80-F-9:AMMRC-TR-80-25) Avail: NTIS HC A05/MF A01 CSCL01/3

A method for predicting the endurance life of the elastomericbearings on the UTTAS helicopter rotor is presented. The criticallayers, based on elastomer strain, are determined analytically forthese two bearings. Representative standard laboratory testspecimens bonded with the specified elastomers are subjectedto the same static and typical dynamic strains, and tested tofailure. Two resulting S-N curves are reported, one for each ofthe two rotor elastomeiic bearings. A short verif ication ofMiner's cumulative damage theory is also conducted andreported. GRA

N81-14325# Pratt and Whitney Aircraft Group, West PalmBeach. Fla. Government Products Div.IMPROVED CAPABILITIES TO DETECT INCIPIENT BEAR-ING FAILURES Final Report. 1 May 1978 - 31 Mar. 1980J. A. Alcorta. J. H. Mohn, and L L. Packer Jul. 1980 86 prefs(Contract F33615-78-C-2008: AF Pro). 3048)(AD-A091687: PWA-FR-13036A: AFWAL-TR-80-2057) Avail:NTIS HC A05/MF A01 CSCL 13/9

A methodology using safe, low level radiation technique forthe detection of wear in gas turbine engine mainshaft bearingshas been developed and evaluated in a simulated gas turbineengine bearing environment. In conjunction with spectrometricanalyses of engine oil samples, the radioactive tag will detectlow levels of wear and will simultaneously indicate whether thetagged bearing is the source of the wear, lron-55 is employedas the active tag owing to its low radiation levels, long half-life,and homogeneity of the isotope in the bearing rollers. The lowlevels of radiation existent in the tagged wear particles requiresthe separation of wear debris from the oil. Test results showedthat the tagging method would provide a means of identifyingthe tagged rollers experiencing abnormal wear at the -f or -0.5 part per million iron level. Safe, low-level radioactivebearing roller tagging was achieved by waiting six months afterneutron irradiation for the decay of the iron-59 and thechromium-51 gamma emitting radioisotopes. Wear measurementsare conducted using the long half-life, low energy emitting X-raysfrom iron-55. The technique used for tagging, debris concentration,debris measurement, and bearing testing is given. GRA

N81-14327# United Technologies Corp.. South Windsor, Conn.Power Systems Div.

N81-14329# Detroit Diesel Allison. Indianapolis. Ind.GAS TURBINE ENGINES AND TRANSMISSIONS FOR BUSDEMONSTRATION PROGRAMS Technical Status Report.31 Jan. - 30 Apr. 1980D. N. Nigro May 1980 7 p(Contract DE-AC02-78CS-54867)(COO-4867-07) Avail: NTIS HC A02/MF A01

Activities related to the procurement and delivery of 1 1 gasturbine engines, 11 automatic transmissions, and software itemssuch as cost reports, drawings and parts lists for the busdemonstration program are reported. DOE

N81-14332# General Electric Co.. Schenectady. N. Y. GasTurbine Div.DEVELOPMENT OF H IG H-TEM PER ATU R E TURBINESUBSYSTEM TECHNOLOGY TO A TECHNOLOGY READI-NESS STATUS. PHASE 2 Quarterly Report. Jul. - Sep.1979M. W. Horner Oct. 1979 172 p(Contract EX-76-C-01-1806)(FE-1806-72) Avail: NTIS HC A08/MF A01

The program was divided into three phases: Program andSystem Definition, Technology Testing and Test Support Studies,and Technology Readiness Verification Test Program. The workscope for the overall three phases of the program encompassesthe design, development, manufacture, and test of a GE-TRVturbine subsystem to be tested at a DOE facility. The objectivesof Phase 2 are to: perform component design and technologytesting in critical areas: perform system design and tradeoffanalyses in sufficient depth to support the component designand test tasks: and update the Phase 1 combined cycle studiesto evaluate the commercial viability of GE-TRV turbine system.

DOE

N81-14347*# California Univ., Los Angeles. Dept. of Mechanicsand Structures.DUAL METHODS AND APPROXIMATION CONCEPTS INSTRUCTURAL SYNTHESIS Final Report. Feb. 1978 - Aug.1979Claude Fleury and Lucien A. Schmit. Jr. Washington NASADec. 1980 223 p refs(Grant NsG-1490)(NASA-CR-3226) Avail: NTIS HC A10/MF A01 CSCL 20K

Approximation concepts and dual method algorithms arecombined to create a method for minimum weight design ofstructural systems. Approximation concepts convert the basicmathematical programming statement of the structural synthesisproblem into a sequence of explicit primal problems of separableform. These problems are solved by constructing explicit dualfunctions, which are maximized subject to nonnegativity con-straints on the dual variables. It is shown that the joining togetherof approximation concepts and dual methods can be viewed asa generalized optimality criteria approach. The dual method is

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successfully extended to deal with pure discrete and mixedcontinuous-discrete design variable problems. The power of themethod presented is illustrated with numerical results for exampleproblems, including a metallic swept wing and a thin delta wingwith fiber composite skins. Author

N81-14363# Pennsylvania Univ.. Philadelphia. Dept. of MaterialsScience and Engineering.MECHANISMS OF DAMAGE ACCUMULATION IN TIME-DEPENDENT CYCLIC DEFORMATION Progress Report.1 Jan. - 31 Dec. 1980Campbell Laird Aug. 1980 15 p refs(Contract DE-AC02-80ER-10570)(DOE/ER-10570/1) Avail: NTIS HC A02/MF A01

Two kinds of damage produced in cyclic creep wereinvestigated. The change in dislocation density and arrangementin copper and damage phenomena involving precipitates inCr-Mo-V rotor steel. In copper tested at low temperatures,strain bursts were recognized for the first time in polycrystals ofa pure metal in both cyclic and static creep. The stress regimefor producing bursts was defined and the dislocation structuresassociated with them studied. Interpretation based on instabilitiesassociated with the persistent slip bands which form in regularfatigue is being explored. For the study of rotor steel, threebatches of material were obtained and characterized and a newhigh temperature apparatus built to do tests. A literature reviewjustifying the choice of steels and tests is provided. HOE

N81-14525$ National Technical Information Service. Springfield.Va.MANEUVERING AIRCRAFT: NOISE POLLUTION ANDCONTROL. CITATIONS FROM THE NTIS DATA BASEProgress Report, 1976 - Aug. 1980Guy E. Habercom. Jr. Sep. 1980 189 p SupersedesNTIS/PS-79/0973 and NTIS/PS-78/0930(PB80-815566; NTIS/PS-79/0973: NTIS/PS-78/0930) Avail:NTIS HC S30.00/MF S30.00 CSCL 13B

Methods for alleviating noise created by maneuvering aircraftare cited. Flyby. turning flight, takeoffs. and landings are themaneuvers investigated. This updated bibliography contains184 citations. 25 of which are new entries to the previousedition. GRA

N81 14550# Los Alamos Scientific Lab.. N. Mex.STATISTICAL RELATIONSHIP BETWEEN MEDIAN VISIBILITY AND CONDITIONS OF W O R S T C A S E MANMADEIMPACT ON VISIBILITYJohn D. Gins (Technology Service Corp.. Santa Monica. Calif.),David Nochumson. and John Trijonis (Santa Fe Research Corp..N. Mex.) 1980 16 p refs Presented at the Symp. on Plumesand Visibility. Grand Canyon. Ariz. 10-14 Nov. 1980(Contract W-7405-eng-36)(LA-UR-80-2485: CONF-801114-1) Avail: NTISHCA02/MF A01

The data base for the study consisted of midday visibilityrecordings for the years 1974 to 1976 at 28 suburban/nonurbanairports throughout the United States. The visibility recordingswere converted to estimates of extinction coefficients with theuse of the Koschmeider formula. The data were sorted accordingto meteorology in order to eliminate days that were obviouslydominated by natural causes of poor visibility. Three approacheswere used for relating worst-case extinction to median extinction.The first approach was based upon frequency distributionfunctions. The second used observed ratios of upper percentileto median extinction. The third employed regression techniques.All ot the relationships were formulated and evaluated with the1974 to 1976 data on a national/annual basis as well asregional/quarterly basis. Performance tests were run against 1954to 1956 data at 11 of the 28 sites. Simple ratio relationshipsare recommended for use in translating median visibility impactsinto worst-case impacts. The errors associated with these ratiomodels are approximately 30%. DOE

N81-14555*# National Aeronautics and Space Administration.Marshall Space Flight Center. Huntsville. Ala.PROCEEDINGS: FOURTH ANNUAL WORKSHOP ONMETEOROLOGICAL AND ENVIRONMENTAL INPUTS TOAVIATION SYSTEMSWalter Frost, ed. and Dennis W. Camp. ed. Mar. 1980 287 prefs Workshop held in Tullahoma, Tenn.. 25-27 Mar^ 1980:sponsored in part by FAA and NOAA Prepared in cooperationwith Tennessee Univ. Space Inst.(Contract NAS8-32692)(NASA-CP-2139: FAA-RD-80-67) Avail: NTISHC A13/MF A01 CSCL 04B

Various aspects of the interaction of the atmosphere withaviation systems are discussed. The topics for discussion addressedthe following: winds and wind shear: turbulence: icing and frost:fog. visibility, and ceiling: and atmospheric electricity and lightning.

N81-14556*# National Aeronautics and Space Administration.Marshall Space Flight Center. Huntsville, Ala.SURVEY OF WORKSHOPS ON METEOROLOGICAL ANDENVIRONMENTAL INPUTS TO AVIATION SYSTEMSWalter Frost (Tennessee Univ. Space Inst.) and Dennis W. CampIn its Proc: Fourth Ann. Workshop on Meteorol. and Environ.Inputs to Aviation Systems Mar. 1980 p 23-39

Avail: NTIS HC A13/MF A01 CSCL 04BVarious aspects of aviation meteorology are discussed with

respect to their relative effects on aircraft terminal operations.Existing data on turbulence and wind shear from aircraft andtowers are summarized. The significance of obtaining more realtime wind and temperature information is emphasized. Theapplication and testing of various radiometer devices are alsodescribed. Airborne methods to indicate wind differences at flightaltitude and at touchdown are reported. R.C.T.

N81-14557*# National Aeronautics and Space Administration.Marshall Space Flight Center, Huntsville. Ala.AVIATION METEOROLOGY RESEARCH AND DEVELOP-MENT: A STATUS REPORTJohn Enders In its Proc: Fourth Ann. Workshop on Meteorol.and Environ. Inputs to Aviation Systems Mar 1980 p 40-44

Avail: NTIS HC A13/MF A01 CSCL 048The dynamic and rapid growth of technology in the area of

aviation meteorology research and development are describedwith emphasis on the measurement of hazardous weatherphenomena. Aspects of both onboard instrumentation andground based facilities are evaluated in terms of their effectivenessof in avoiding hazards due to atmospheric electricity and lightning.Methods of alleviating terminal are hazards such as fog. lowvisibility and ceilings are also described. R.C.T.

N81-14558*# National Aeronautics and Space Administration.Marshall Space Flight Center. Huntsville.-Ala.FEDERAL AVIATION ADMINISTRATION AND NATIONALWEATHER SERVICE AVIATION RESEARCH AND DEVELOP-MENTJohn W. Connolly In its Proc: Fourth Ann. Workshop on Meteorol.and Environ. Inputs to Aviation Systems Mar. 1980 p 45-48

Avail: NTIS HC A13/MF A01 CSCL 04BAn overview is given of the developmental status of aviation

weather services. Particular attention is given to justifying theneed for better, more reliable service. The accomplishments ofseveral automatic weather stations are discussed. R.C.T.

N81-14560*# Army Test and Evaluation Command. AberdeenProving Ground. Md.AIRCRAFT ICING INSTRUMENTATION: UNFILLEDNEEDSPhyllis F. Kitchens In NASA. Marshall Space Flight CenterProc: Fourth Ann. Worksnop on Meteorol. and Environ. Inputsto Aviation Systems Mar 1980 p 61-65Avail: NTIS HC A13/MF A01 CSCL 04B

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A list of icing instrumentation requirements are presented.Because of the Army's helicopter orientation, many of thesuggestions are specific to rotary wing aircraft: however, someof the instrumentation are also suitable for'general aviationaircraft. R.C.T.

N81-14561*# Lockheed Aircraft Service Co.. Pasadena. Calif.TURBULENCE: FROM A PILOT'S VIEWPOINTCharles L. Pocock In NASA. Marshall Space Flight CenterProc: Fourth Ann. Workshop on Meteorol. and Environ. Inputsto Aviation Systems Mar. 1980 p 66-70

Avail: NTIS HC A13/MF A01 CSCL 04BThe measurement of atmospheric turbulence is discussed in

terms of a pilots viewpoint. Two areas of measurement areconsidered: frequency and severity of turbulence. Suggestionsare given for helping the pilot solve the turbulence problem.

R.C.T.

N81-14562*# National Aeronautics and Space Administration.Hugh L. Dryden Flight Research Center. Edwards. Calif.CLEAR AIR TURBULENCE: HISTORICAL COMMENTSL. J. Ehernberger In NASA. Marshall Space Flight CenterProc: Fourth Ann. Workshop on Meterol. and Environ. Inputsto Aviation Systems Mar. 1980 p 71-81 refs

Avail: NTIS HC A13/MF A01 CSCL 04BThe basic reference material for gust design criteria are cited.

The status of clear air turbulence meteorology (forecasting anddetection) is discussed. The directions of further researchtechnology is indicated. R.C.T.

N81-14563*# Federal Aviation Administration, Atlantic City,N.J,WINDS AND WIND SHEAR IN-SITU SENSORSR. Craig Goff In NASA. Marshall Space Flight Center Proc:Fourth Ann. Workshop on Meteorol. and Environ. Inputs to AviationSystems Mar. 1980 p 82-108

Avail: NTIS HC A13/MF A01 CSCL 04BThe problem of development of instrumentation for providing

wind speed and direction information directly or indirectly to apilot in the cockpit is considered. The pilots need for horizontalwind information at various stages of flight {i.e., at liftoff, inapproach and departure corridors, and even in flight outside theterminal area) are emphasized. R.C.T.

N81-14566*# Aeronautical Systems Div., Wright-Patterson AFB,Ohio.OBSERVING LIGHTNING FROM GROUND-BASED ANDAIRBORNE STATIONSJohn C. Corbin. Jr. In NASA. Marshall Space Flight CenterProc.: Fourth Ann. Workshop on Meteorol. and Environ. Inputsto Aviation Systems Mar. 1980 p 130-139 refs

Avail: NTIS HC A13/MF A01 CSCL 048The operational designs and performance capabilities of

ground-based and airborne lightning detection systems arereviewed. The airborne Stormscope system is described andcompared with onboard radar and the lightning detection andranging system (LDAR). Two examples of difference-in-time-of-arrival systems for detecting spherics from discharges in electrifiedclouds are described: (1) The LDAR system and (2) Taylor'slightning mapping system. Next, an interferometric systemadapted to lightning location is discussed. Finally, systems thatare based upon crossed-loop magnetic direction finding principlesbut which have been refined and improved to accurately locatelightning discharges to ground are reviewed. M.G.

N81-14567*# National Aeronautics and Space Administration.Marshall Space Flight Center, Huntsville. Ala.AERONAUTICAL CONCERNS AND NATIONAL AERONAU-TICS AND SPACE ADMINISTRATION ATMOSPHERICELECTRICITY PROJECTS

William W. Vaughan In its Proc.: Fourth Ann. Workshop onMeteorol and Environ. Inputs to Aviation Systems Mar. 1980p 140-160Avail: NTIS HC A13/MF A01 CSCL 048

The phenomenology of lightning and lightning measurementtechniques are briefly examined with a particular reference toaeronautics. Developments made in airborne and satellite detectionmethods are reported. NASA research efforts are outlined whichcover topics including in-situ measurements, design factors andprotection, remote optical and radio frequency measurements,and space vehicle design. M.G.

N81-14568*# Federal Aviation Administration. Washington. D.C.Systems Research and Development Service.MEASURING WEATHER FOR AVIATION SAFETY IN THE1980'SRobert W. Wedan In NASA. Marshall Space Flight CenterProc.: Fourth Ann. Workshop on Meteorol. and Environ. Inputsto Aviation Systems Mar. 1980 p 162-167

Avail: NTIS HCA13/MFA01 CSCL 04BRequirements for an improved aviation weather system are

defined and specifically include the need for (1) weatherobservations at all airports with instrument approaches,(2) more accurate and timely radar detection of weather elementshazardous to aviation, and (3) better methods of timely distributionof both pilot reports arhd ground weather data. The developmentof the discrete address beacon system data link, Doppler weatherradar network, and various information processing techniquesare described. M.G.

N81-14571*j{/ National Oceanic and Atmospheric Administration,Boulder. Colo. Environmental Research Labs.THE MICROBURST: COMMON FACTOR IN RECENTAIRCRAFT ACCIDENTSFernando Caracena In NASA. Marshall Space Flight CenterProc.: Fourth Ann. Workshop on Meteorol. and Environ. Inputsto Aviation Systems Mar. 1980 p 186-200 refs

Avail: NTIS HC A13/MF A01 CSCL 04BThe phenomenology of one class of strong thunderstorm

downdrafts, microbursts, is described. Several aircraft accidentsare analyzed in which a microburst was involved and a conceptfor an early warning wind shear sensor is presented. M.G.

N81-14572*# National Center for Atmospheric Research.Boulder. Colo.DOCTOR FUJITA'S MICROBURST ANALYSIS AT CHICAGOJohn McCarthy In NASA. Marshall Space Flight Center Proc.:Fourth Ann. Workshop on Meteorol. and Environ. Inputs to AviationSystems Mar. 1980 p 201-202

Avail: NTIS HC A13/MF A01 CSCL 046Doppler radar measurements of an intense wind shear

occurance are discussed. The data suggest the presence of anincredibly strong low level jet outflow component of the microburstevent, reaching 60 knots only 50 meters above the surface.Evidence also suggests that microbursts more typically occur invery weak thunderstorms that have hardly reached thunderstormstage. M.G.

N81-14575# Weapons Systems Research Lab.. Adelaide(Australia).LOW-SPEED WIND-TUNNEL TESTS OF TWO WEATHER-COCKING SENSORSD. P. Brown and R. I. Macleod Aug. 1980 29 p refs(WSRL-0171-TM: AR-002-036) Avail: NTISHC A03/MF A01

Two blunt-nosed weathercocking wind direction sensors, onestabilized by a ring tail and the other by swept cruciform fins,were tested in a low-speed wind tunnel to investigate possibleaerodynamic interference between these wind direction sensorsand the vehicles in front of which they were to be mounted. In

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these low speed tests, sensor support shaft diameter and vehiclenose tip geometry both caused significant errors in the ring-tailedsensor's alignment to the free stream when the vehicle was atangle of attack. A disk baffle placed on the shaft behind thesensor base was found to reduce sensor misalignment significantlyat small angles of attack. Alignment errors for the cruciformsensor were much smaller than those of the ring-tailed sensorat small angles of attack, and these smaller errors were furtherreduced when a baffle was placed on the shaft. Author

N81-14601*# EG and G Washington Analytical Services Center.Inc.. Pocomoke City. Md.CATALOG OF SEA STATE AND WIND SPEED IN THESOUTH ATLANTIC BIGHTJ. D. McMillan Jan. 1980 134 p refs(Contract NAS6-2639)(NASA-CR-156872) Avail: NTIS HC A07/MF A01 CSCL08C

The GEOS 3 significant waveheight and ground wind speedestimation algorithms are derived and then applied to all GEOS3 data in the South Atlantic Bight. The investigation area isdivided into five geographical sectors and significant waveheightand wind speed histograms are presented in each sector bymonth and by season. In the discussion of the histograms, definiteseasonal trends are identified and examined. Author

N81-14697*# Lockheed-Georgia Co.. Marietta.COMPONENT-ADAPTIVE GRID EMBEDDINGE. H. Atta In NASA. Langley Research Center NumericalGrid Generation Tech. 1980 p 157-174 ref

Avail: NTIS HC A24/MF A01 CSCL 12AOne of the major problems related to transonic flow

prediction about realistic aircraft configuration is the generationof a suitable grid which encompasses such configurations. Ingeneral, each aircraft component (wing, fuselage, nacelle) requiresa grid system that is usually incompatible with the grid systemsof the other components: thus, the implementation of finite-difference methods for such geometrically-complex configurationsis a difficult task. An approach was developed to treat such aproblem. The basic idea is to generate different grid systems,each suited for a particular component. Thus, the flow field domainis divided into overlapping subdomains of different topology. Thesegrid systems are then interfaced with each other in such a waythat stability, convergence speed and accuracy are maintained.

Author

N81-14708*/? Aircraft Research Association Ltd. Bedford(England).AN INVESTIGATION INTO GRID PATCHING TECH-NIQUESC. R. Forsey, M. G. Edwards, and M. P. Carr In NASA. LangleyResearch Center Numerical Grid Generation Tech. 1980p 265-294 Sponsored in part by the Ministry of Defence, England

Avail: NTIS HC A24/MF A01 CSCL 12AIn the past decade significant advances were made using

flow field methods in the calculation of external transonic flowsover aerodynamic configurations. It is now possible to calculateinviscid transonic flow over three dimensional configurations bysolving the potential equation. However, with the exception ofthe transonic small disturbance methods which have the advantageof a simple cartesian grid, the configurations over which it ispossible to calculate such flows are relatively simple. The majorreason for this is the difficulty of producing compatibility between,grid generation and flow equation solutions The main programsin use. use essentially analytic transformations for prescribedconfigurations and, as such, are not easy to extend. While thereis work in progress to extend this type of system to a limitedextent, the long term effort is directed towards a more generalapproach. This approach should not be restricted to producinggrid systems in isolation but rather a consideration of the overallproblem of flow field solution. E.D.K.

N81-14714*)Sf Boeing Co.. Seattle. Wash.GRID GENERATION FOR GENERAL THREE-DIMENSIONALCONFIGURATIONSK. D. Lee. M. Huang. N. J. Yu, and P. E. Rubbert In NASA.Langley Research Center Numerical Grid Generation Tech. 1980p 355-366Avail: NTIS HC A24/MF A01 CSCL 12A

A suitable grid system for complex three dimensionalconfigurations such as wing/body/nacelle shape for the solutionof nonlinear transonic flow problems was constructed. Twoapproaches were explored based on Thompson's body fittedcoordinate concept. The most general approach was to dividethe computational domain into multiple rectangular blocks wherethe configuration itself was also represented by a set of blockswhose structure follows the natural lines of the configuration.The block structured grid system was adaptable to complexconfigurations and gives good grid quality near physical corners.However, it introduced algorithm issues for the flow solutionconcerning the treatment of nonanalytic grid block boundariesand nonstandard grid cells. These issues were explored in relationto the grid generation. A more limited approach treats a wing/bodyconfiguration with only a single rectangular block in computationalspace. The issues involving nonstandard cells were avoided, butother limitations on grid resolution appear. Both a linear and anonlinear system of grid generation equations were developedincluding methods of grid control. R.C.T.

N81-14788*# National Aeronautics and Space Administration.Langley Research Center, Hampton, Va.ASSESSMENT OF GROUND EFFECTS ON THE PROPAGA-TION OF AIRCRAFT NOISE: THE T-38A FLIGHT EXPERI-MENTWilliam L Willshire, Jr. Dec. 1980 128 p refs(NASA-TP-1747: L-13765) Avail: NTIS HC A07/MF A01CSCL 20A

A flight experiment was conducted to investigate air to groundpropagation of sound at gazing angles of incidence. A turbojetpowered ariplane was flown at altitudes ranging from 10 to160 m over a 20-microphone array positioned over grass andconcrete. The dependence of ground effects on frequency,incidence angle, and slant range was determined using twoanalysis methods. In one method, a microphone close to theflight path is compared to down range microphones. In theother method, comparisons are made between two microphoneswhich were equidistant from the flight path but positioned overthe two surfaces. In both methods, source directivity angle wasthe criterion by which portions of the microphone signals werecompared. The ground effects were largest in the frequencyrange of 200 to 400 Hz and were found to be dependent onincidence angle and slant range. Ground effects measured forangles of incidence greater than 10 deg to 15 deg were nearzero. Measured attenuation increased with increasing slant rangefor slant ranges less than 750 m. Theoretical predictions werefound to be in good agreement with the major details of themeasured results. Author

N81-14789*# Georgia Inst. of Tech., Atlanta. School ofAerospace Engineering.PREDICTION OF SOUND RADIATED FROM DIFFERENTPRACTICAL JET ENGINE INLETS Semiannual Status Report.2 Jun. - 30 Nov. 1980B. T. Zinn and W. L Meyer 1980 41 p refs(Grant NAG3-67: Contract F49620-77-C-0066)(NASA-CR-163824) Avail: NTIS HC A03/MF A01 CSCL20A

Existing computer codes for calculating the far field radiationpatterns surrounding various practical jet engine inlet configura-tions under different excitation conditions were upgraded. Thecomputer codes were refined and expanded so that they arenow more efficient computationally by a factor of about threeand they are now capable of producing accurate results up tonondimensional wave numbers of twenty. Computer programswere also developed to help generate accurate geometricalrepresentations of the inlets to be investigated. This data isrequired as input for the computer programs which calculatethe sound fields. This new geometry generating computer programconsiderably reduces the time required to generate the input

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data which was one of the most time consuming steps in theprocess. The results of sample runs using the NASA-Lewis QCSEEinlet are presented and comparison of run times and accuracyare made between the old and upgraded computer codes. Theoverall accuracy of the computations is determined by comparisonof the results of the computations with simple source solutions.

A.R.H.

N81-14792$ National Physical Lab.. Teddington (England).Acoustics Unit.THE RATING OF HELICOPTER NOISE: DEVELOPMENTOF A PROPOSED IMPULSE CORRECTIONB. F. Berry. H. C. Fuller. A. J. John, and D. W. Robinson Dec.1979 45 p refs(NPL-AC-93; ISSN-0143-7143) Avail: NTISHC A03/MF A01

Efforts to the scale of effective perceived noise level (EPNL)to account for the subjective effects of impulsive helicopter noiseare reported. Psychoacoustical studies of the annoyance ofrecorded and simulated helicopter noises are described and anobjective descriptor of impulsiveness is developed. This descriptorforms the basis of a draft standard for an impulse correction toEPNL M.G.

N81-14793# Rolls-Royce Ltd.. Derby (England).EXHAUST NOISE IN FLIGHT: THE ROLE OF ACOUSTICINSTALLATION EFFECTSI. S. Southern Apr. 1980 14 p refs(PNR-90029) Avail: NTIS HC A02/MF A01

The acoustic installation effect on engine exhaust noise dueto the presence of a wing or high tailplane is discussed forboth the static and flight cases. A simple theoretical model forreflection and edge diffraction using ray theory is introducedand compared with experimental results. The model is used topredict full scale installation effects where, due to the lowdirectivity of engine noise, reflection is dominant and the effectgenerally less than 3 dB. This suggests that the so called staticto flight anomaly cannot be explained in terms of acousticinstallation effects. Some alternative possibilities are reviewed.

Author

N81-14795# Rolls-Royce Ltd.. Derby (England).THE MEASUREMENT OF AERO GAS TURBINE NOISEL. R. Bentley 29 Jan. 1980 44 p refs(PNR-90032) Avail: NTIS HC A03/MF A01

Equipment used in noise certification tests for gas turbineaircraft engines includes: (1) a microphone system, calibratedamplifier and tape recorder: (2) a means of relating aircraftposition and the noise: and (3) an apparatus for determiningthe temperature and humidity conditions in the propagation spacefor the calculation of atmospheric attenuation. Techniques forobtaining flyover and static test bed measurements are examinedand assessed. Future developments are considered with emphasison the acquisition of digital data. A.R.H.

N81-14796# Deutsche Forschungs- und Versuchsanstalt fuerLuft- und Raumfahrt. Goettingen (West Germany). Inst. fuerExperimentelle Stroemungsmechanik.NOISE AND NOISE ABATEMENT IN FANS AND BLOWERS:A REVIEWWolfgang Neise Mar. 1980 148 p refs In GERMAN: ENGLISHsummary(DFVLR-FB-80-16) Avail: NTIS HC A07/MF A01: DFVLR.Cologne DM 22.50

Noise generation and its reduction industrial fans (ventilators)is addressed. A review is given of the fan types commonly inuse and their practical applications, the mechanisms of theaerodynamic noise generation in fans, theoretical and empiricalprediction methods for fan noise, acoustic similarity laws, andnoise reduction methods by means of the fan construction andfan operation. Measurement procedures are discussed with respectto the noise radiated from different parts of a fan. e.g.. from thefan inlet or outlet, from the fan casing, from the fan as a whole,and to the noise radiated into ducts connected to the fan. Finally.

considerations are made, for which classes of fans noise standardscan be defined to characterize the noise emission of the variousfan types. M.G.

N81-14962*# National Aeronautics and Space Administration.Washington. 0. C.BIRD FLIGHT AND AIRPLANE FLIGHTA. Magnan Dec. 1980 424 p refs Transl. into ENGLISHfrom Serv. Tech. de I'Aeron. (Paris), bull. 74. Jun. 1931 p 5-307Transl. by Kanner (Leo) Associates. Redwood City. Calif.(Contract NASw-3199)(NASA-TM-75777) Avail: NTIS HC A18/MF A01 CSCL01B

Research was based on a series of mechanical, electrical,and cinematographic instruments developed to measure variousfeatures of air current behavior as well as bird and airplaneflight. Investigation of rising obstruction and thermal currentsled to a theory of bird flight, especially of the gliding andsoaring types. It was shown how a knowledge of bird flight canbe applied to glider and ultimately motorized aircraft construction.The instruments and methods used in studying stress in airplanesand in comparing the lift to drag ratios of airplanes and birdsare described. T.M.

N81-14964 Air Force Inst. of Tech.. Wright-Patterson AFB,Ohio.TIME DEPENDENT NAVIER-STOKES SOLUTION OF ATURBULENT GAS JET EJECTED FROM A RECTANGULARORIFICE INTO A HIGH-SUBSONIC CROSSFLOWPh.D. ThesisWilliam Charles Golbitz 1980 187 pAvail: Univ. Microfilms Order No. 8028555

The high temperature (1500K) exhaust gases from anairborne chemical laser being forcibly ejected downwards at ajet to freestream dynamic pressure ratio (Q) of 0.15 from anaspect ratio 1.75 rectangular diffuser orifice aligned with themajor axis parallel to the mach 0.7 ambient crossflow at thetropopause was successfully simulated using a modified donor-cellICE (Implicit Continuous fluid Eulerian) algorithm formulated inprimitive variables. The complete set of time dependent,three-dimensional Navier-Stokes equations and a speciesconservation equation were numerically solved for every cell inthe computational domain. The diffusive flux effects caused byconcentration gradients (Fick's Law) as well as variable transportand thermodynamic properties of the gas mixture were incorpor-ated into the numerical model Turbulence closure was achievedby employing a locally varying velocity defect eddy viscositymodel. Chemical reactions between the exhaust gases and theambient crossflow were proscribed. Dissert. Abstr.

N81-14966 Wichita State Univ.. Kans.AN ANALYTIC MODEL OF SUBSONIC FLOW AROUND ANAIRFLOW WITH A SPOILER Ph.D. ThesisNeal Jay Pfeiffer 1980 103 pAvail: Univ Microfilms Order No. 8028606

A computer model was developed to simulate low speedtwo dimensional flow past the airfoil Flow visualization and windtunnel measurements provided insight into the basic physicalfeatures of this flow. The basis of the method was the matchingof solutions for outer and inner regions. Once the inner andouter solutions were compatible, surface pressures were integratedto give values of lift. drag, pitching moment and spoiler hingemoment coefficients. Corrections for skin friction were included.Computations were made for two low speed airfoils for whichdetailed data exist for flow with spoilers. The comparisons coveredranges of spoiler deflection angles up to 60 deg and angles ofattack from zero to full stall. T.M.

N81-14967* National Aeronautics and Space Administration.John F. Kennedy Space Center, Cocoa Beach. Fla.SYSTEM FOR REFURBISHING AND PROCESSING PARA-CHUTES PatentRussell T. Crowell. inventor (to NASA) Issued 30 Sep. 19808 p Filed 21 Dec. 1977 Supersedes N78-22026 (16 - 13.p 1654)

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(NASA-Case-KSC-11042-1; US-Patent-4,224.810:US-Patent-Appl-SN-862878: US-Patent-Class-68-3R) Avail: USPatent and Trademark Office CSCL 13H

A method for refurbishing and processing parachutes isdisclosed including an overhead monorail conveyor system onwhich the parachute is suspended for horizontal conveyance.The parachute is first suspended in partially open tentedconfiguration wherein open inspection of the canopy is permitted.The parachute is transported by the monorail conveyor to awashing and drying station. Following drying of the parachute,the parachute is conveyed into an interior space where it isfinally inspected and removed from the monorail conveyor andlaid upon a table for folding. Following folding operations, theparachute is once again mounted on the conveyor in an elongatedhorizontal configuration and conveyed to a packing area forstowing the parachute in a deployment bag.

Official Gazette of the U.S Patent and Trademark Office

N81-14968* National Aeronautics and Space Administration.Langley Research Center, Hampton. Va.AERODYNAMIC SIDE-FORCE ALLEVIATOR MEANSPatentDhanvada M. Rao. inventor (Old Dominion Univ.) Issued 30 Sep1980 7 p Filed 12 Mar 1979 Supersedes N79-17813 (17 -09. p 1072) Sponsored by NASA(NASA-Case-LAR-12326-1; US-Patent-4,225.102;US-Patent-Appl-SN-019541; US-Patem-Class-244-130;US-Patent-Class-102-56R: US-Patent-Class-102-92.1;US-Patent-Class-244-119) Avail: US Patent and TrademarkOffice CSCL 01A

An apparatus for alleviating high angle of attack side forceon slender pointed cylindrical forebodies such as fighter aircraft,missiles and the like is described. A symmetrical pair of helicalseparation trips was employed to disrupt the leeside vorticesnormally attained. The symmetrical pair of trips starts at eithera common point or at space points on the upper surface of theforebody and extends along separate helical paths along thecircumference of the forebody.

Official Gazette of the US Patent and Trademark Office

N81-14969$ National Aerospace Lab.. Amsterdam (Netherlands).TRANSONIC WIND TUNNEL TESTS ON AN OSCILLATINGWING WITH EXTERNAL STORE. PART 4: THE WINGWITH UNDERWING: STORE Final Report, Feb. 1977 -Sep. 1979H. Tijdeman, J. W. G vanNunen, A. N. Draan, A. J. Persoon, R.Poestkoke, R. Roos, P. Schnippers. and C M Siebert Wright-Parterson AFB. Ohio AFFDL Sep. 1979 178 p refs(Grant AF-AFOSR-3233-77)(AD-A077370: AFFD L-TR-78-194-PI-4; NLR-TR-78106-U)Avail: NTIS HCA09/MFA01 CSCL01A

Detailed steady and unsteady pressure distributions wereobtained over the wing, while on the store total aerodynamicloads were measured. The tests covered the Mach number rangebetween Ma = 0.6 and Ma = 1.35, and reduced frequenciesranging up to k = 0.4 at Ma = 0.6 and to k = 02 at Ma =1.35. Emphasis was put on the influence of the pylon and storeon the wing loading and further on the loads acting on thepylon and store itself. A comparison is presented of experimen-tal data and theoretical results obtained with the unsteady NLRIand Doublet Lattice methods. T.M.

N81-14970*# Boeing Commercial Airplane Co., Seattle, Wash.A SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSISOF SUPERSONIC A IRCRAFT. PART 1: GENERALDESCRIPTION AND THEORETICAL DEVELOPMENT FinalReport. Sep. 1978 - Aug. 1980W. D. Middleton and J. L. Lundry Washington NASA Dec.1980 101 p refs(Contract NAS1-15534)(NASA-CR-3351; 06-41840-1) Avail: NTISHC A06/MF A01 CSCL 01A

An integrated system of computer programs was developedfor the design and analysis of supersonic configurations. Thesystem uses linearized theory methods for the calculation ofsurface pressures and supersonic area rule concepts in combination

with linearized theory for calculation of aerodynamic forcecoefficients. R.C.T.

N81-14971*# Boeing Commercial Airplane Co.. Seattle. Wash.A SYSTEM FOR AERODYNAMIC DESIGN AND ANALYSISOF SUPERSONIC AIRCRAFT. PART 3: COMPUTERPROGRAM DESCRIPTION Final Report. Sep. 1978 - Aug.1980W. D. Middleton, J. L. Lundry, and R. G. Coleman WashingtonNASA Dec. 1980 122 p refs(Contract NAS1-15534)(NASA-CR-3353: D6-41840-3) Avail: NTISHC A06/MF A01 CSCL 01A

The computer program documentation for the design andanalysis of supersonic configurations is presented. Schematicsand block diagrams of the major program structure, togetherwith subroutine descriptions for each module are included.R.C.T.

N81-14972*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.INVESTIGATION OF CONVERGENT-DIVERGENT NOZZLESAPPLICABLE TO REDUCED-POWER SUPERSONIC CRUISEAIRCRAFTBobby L. Berrier and Richard J. Re Dec. 1980 218 p refs(NASA-TP-1766: L-13974) Avail: NTIS HC A10/MF A01CSCL 01A

An investigation was conducted of isolated convergent-divergent nozzles to determine the effect of several designparameters on nozzle performance. Tests were conducted usinghigh pressure air for propulsion simulation at Mach numbersfrom 0 60 to 2.86 at an angle of attack of 0 deg and at nozzlepressure ratios from jet off to 460. Three power settings (dry.partial afterburning, and maximum afterburning), three nozzlelengths, and nozzle expansion ratios from 1.22 to 2.24 wereinvestigated. In addition, the effects of nozzle throat radius anda cusp in the external boattail geometry were studied. The resultsof this study indicate that, for nozzles operating near designconditions, increasing nozzle length increases nozzle thrust-minus-drag performance. Nozzle throat radius and an external boattailcusp had negligible effects on nozzle drag or internal perfor-mance. Author

N81-14973*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.BIBLIOGRAPHY OF SUPERSONIC CRUISE R E S E A R C H(SCR) PROGRAM FROM 1977 TO MID-1980Sherwood Hoffman Dec. 1980 106 p(NASA-RP-1063; L-13764) Avail: NTIS HC A06/MF A01CSCL 01A

The supersonic cruise research (SCR) program, initiated inJuly 1972, includes system studies and the following disciplines:propulsion, stratospheric emission impact, structures and materials,aerodynamic performance, and stability and control. In acoordinated effort to provide a sound basis for any futureconsideration that may be given by the United States to thedevelopment of an acceptable commercial supersonic transport,integration of the technical disciplines was undertaken, analyticaltools were developed, and wind tunnel, flight, and laboratoryinvestigations were conducted. The present bibliography coversthe time period from 1977 to mid-1980. It is arranged accordingto system studies and the above five SCR disciplines. There are306 NASA reports and 135 articles, meeting papers, and companyreports cited. E.D.K.

N81-14974*# National Aeronautics and Space Administration.Langley Research Center. Hampton, Va.LEADING-EDGE DEFLECTION OPTIMIZATION FOR AHIGHLY SWEPT ARROW WING CONFIGURATIONPaul L. Coe, Jr.. Jarrett K. Huffman, and James W. FenbertDec. 1980 59 p refs(NASA-TP-1777; L-13820) Avail: NTIS HC A04/MF A01CSCL 01A

Tests were also conducted to determine the sensitivity ofthe lateral stability derivative C sub I sub beta to geometricanhedral. The optimized leading edge deflection was developed

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by aligning the leading edge with the incoming flow along theentire span. Owing to the spanwise variation of upwash, theresulting optimized leading edge was a smooth, continuouslywarped surface. For the particular configuration studied, levelsof leading edge suction on the order of 90 percent were achievedwith the smooth, continuously warped leading edge contour. Theresults of tests conducted to determine the sensitivity of C subI sub beta to geometric anhedral indicate values of delta C subI sub beta/delta T which are in reasonable agreement withestimates provided by simple vortex lattice theories. T.M.

N81-14975*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.WIND-TUNNEL MEASUREMENTS AND COMPARISONWITH FLIGHT OF THE BOUNDARY LAYER AND HEATTRANSFER ON A HOLLOW CYLINDER AT MACH 3Robert L. Stallings. Jr.. and Milton Lamb Dec. 1980 48 prefs(NASA-TP-1789; L-14044) Avail: NTIS HC A03/MF A01CSCL 01A

The wind tunnel tests were conducted both with and withoutboundary layer trips at Mach 3 and nominal free stream Reynoldsnumbers per meter ranging from 3.3 x 10 the 6th power.Instrumentation consisted of pressure orifices, thermocouples, aboundary layer pilot pressure rake, and a floating element skinfriction balance. Measurements from both wind tunnel and flightwere compared with existing engineering prediction methods.

T.M.

N81-14976*# Detroit Diesel Allison. Indianapolis. Ind.EXPERIMENTAL DETERMINATION OF UNSTEADY BLADEELEMENT AERODYNAMICS IN CASCADES. VOLUME 2:TRANSLATION MODE CASCADE Final ReportR. E. Riffel and M. D. Rothrock Dec. 1980 183 p refs(Contract NAS3-20055)(NASA-CR-165166: EDR-10361-Vol-2) Avail: NTISHC A09/MF A01 CSCL 01A

A two dimensional cascade of harmonically oscillating airfoilswas designed to model a near tip section from a rotor whichwas known to have experienced supersonic translational modelflutter. This five bladed cascade had a solidity of 1.52 and asetting angle of 0.90 rad. Unique graphite epoxy airfoils werefabricated to achieve the realistic high reduced frequency levelof 0.15. The cascade was tested over a range of static pressureratios approximating the blade element operating conditions ofthe rotor along a constant speed line which penetrated the flutterboundary. The time steady and time unsteady flow fieldsurrounding the center cascade airfoil were investigated. Author

N81-14977*# National Aeronautics and Space Administration.Lewis Research Center, Cleveland. Ohio.FINITE ELEMENT ANALYSIS OF INVISCID SUBSONICBOATTAIL FLOWR. V. Chima and P. M. Gerhart (Akron Univ.. Ohio) 1981 16 prefs Presented at the Nineteenth Aerospace Sci. Meeting.St. Louis. 12-15 Jan. 1981: sponsored by Am. Inst. of Aeronauticsand Astronautics(NASA-TM-81650: E-651) Avail: NTIS HC A02/MF A01 CSCL01A

A finite element code for analysis of inviscid subsonic flowsover arbitrary nonlifting planar or axisymmetric bodies is described.The code solves a novel primitive variable formulation of thecoupled irrotationality and compressible continuity equations.Results for now over a cylinder, a sphere, and a NACA 0012 airfoilverify the code. Computed subcritical flows over an axisymmetricboattailed afterbody compare well with finite difference resultsand experimental data. Interative coupling with an integralturbulent boundary layer code shows strong viscous effects onthe inviscid flow. Improvements in code efficiency and exten-sions to transonic flows are discussed. Author

N81-14978*$ National Aeronautics and Space Administration.Lewis Research Center. Cleveland. Ohio.SUPERSONIC STALL FLUTTER OF HIGH SPEED FANS

J J. Adamczyk. W. Stevens, and R. Jutras (GE Co.. Evendale.Ohio) 1981 15 p refs Proposed for presentation at 26thAnn. Intern. Gas Turbine Conf.. Houston, 8-12 Mar. 1981:sponsored by Am. Soc. of Mech. Engr.(NASA-TM-81613: E-612) Avail: NTIS HC A02/MF A01 CSCL01A

An analytical model is developed.for predicting the onset ofsupersonic stall bending flutter in axial flow compressors. Theanalysis is based on a modified two dimensional, compressible,unsteady actuator disk theory. It is applied to a rotor blade rowby considering a cascade of airfoils whose geometry and dynamicresponse coincide with those of a rotor blade element at85 percent of the span height (measured from the hub). Therotor blades are assumed to be unshrouded (i.e., free standing)and to vibrate in thejr first flexural mode. The effects of shockwaves and flow separation are included in the model throughquasi-steady, empirical, rotor total-pressure-loss and deviation-angle correlations. The actuator disk model predicts the unsteadyaerodynamic force acting on the cascade blading as a functionof the steady flow field entering the. cascade and the geometryand dynamic response of the cascade. Calculations show thatthe present model predicts the existence of a bending fluttermode at supersonic inlet Mach numbers. This flutter mode issuppressed by increasing the reduced frequency of the systemor by reducing the steady state aerodynamic loading on thecascade. The validity of the model for predicting flutter isdemonstrated by correlating the measured flutter boundary of ahigh speed fan stage with its predicted boundary. This correlationuses a level of damping for the blade row (i.e.. the log decrementof the rotor system) that is estimated from the experimentalflutter data. The predicted flutter boundary is shown to be ingood agreement with the measured boundary. Author

N81-14979*# National Aeronautics and Space Administration.Lewis Research Center. Cleveland. Ohio.SOLUTION OF PLANE CASCADE FLOW USING IMPROVEDSURFACE SINGULARITY METHODSEric R. McFarland 1981 14 p refs Presented for presentationat 26th Ann. Intern. Gas Turbine Conf., Houston 8-12 Mar.1981: sponsored by Am. Soc. of Mech. Engr.(NASA-TM-81589: E-568) Avail: NTIS HC A02/MF A01 CSCL01A

A solution method was developed for calculating compressibleinviscid flow through a linear cascade of arbitrary blade shapes.The method uses advanced surface singularity formulations whichwere adapted from those in current external flow analyses. Theresulting solution technique provides a fast flexible calculationfor flows through turbomachinery blade rows. The solution methodand some examples of the method's capabilities are presented.

Author

N81-14980*# National Aeronautics and Space Administration.Lewis Research Center. Cleveland. Ohio.FULL POTENTIAL SOLUTION OF TRANSONIC QUASI 3DFLOW THROUGH A C A S C A D E USING ARTIFICIALCOMPRESSABILITYC. Farrell and J. Adamczyk 1981 40 p refs Presented at26th Ann. Intern. Gas Turbine Conf.. Houston. Tex.. 8-12 Mar.1981: sponsored by ASME(NASA-TM-81637: E-574) Avail: NTIS HC A03/MF A01 CSCL01A

The three-dimensional flow in a turbomachinery blade rowwas approximated by correcting for streamtube convergence andradius change in the throughflow direction. The method is afully conservative solution of the full potential equation incorpora-ting the finite volume technique on body fitted periodic mesh,with an artificial density imposed in the transonic region to insurestability and the capture of shock waves. Comparison of resultsfor several supercritical blades shows good agreement with theirhodograph solutions. Other calculations for these profiles as wellas standard NACA blade sections indicate that this is a usefulscheme analyzing both the design and off-design performanceof turbomachinery blading. T.M.

N81-14981*# National Aeronautics and Space Administration.Ames Research Center. Moffett Field, Calif

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EXPERIMENTAL AERODYNAMIC CHARACTERISTICS OFTWO V/STOL FIGHTER/ATTACK AIRCRAFT CONFIGURA-TIONS AT MACH NUMBERS FROM 0.4 TO 1.4Walter P. Nelms. Donald A. Durston. and J. R. Lummus (GeneralDynamics. Fort Worth. Tex.) Dec. 1980 529 p refs(NASA-TM-81234: A-8338) Avail: NTIS HC A23/MF A01CSCL 01A

A wind tunnel test was conducted to measure the aerodynamiccharacteristics of two horizontal attitude takeoff and landingV/STOL fighter/attack aircraft concepts. In one concept, a jetdiffuser ejector was used for the vertical lift system: the otherused a remote augmentation lift system (RALS). Wind tunneltests to investigate the aerodynamic uncertainties and to establisha data base for these types of concepts were conducted over aMach number range from 0.2 to 2.0. The present report coverstests, conducted in the 1 1 foot transonic wind tunnel, for Machnumbers from 0.4 to 1.4. Detailed effects of varying the angleof attack (up to 27 deg). angle of sideslip (-4 deg to +8 deg).Mach number. Reynolds number, and configuration buildup wereinvestigated. In addition, the effects of wing trailing edge flapdeflections, canard incidence, and vertical tail deflections wereexplored. Variable canard longitudinal location and different shapesof the inboard nacelle body strakes were also investigated.

E.D.K.

N81-14983# National Aerospace Lab. Tokyo (Japan).A METHOD FOR OBTAINING SHOCKLESS TRANSONICFLOWS PAST AIRFOILS. PARTIALLY MODIFIED FROM AGIVEN ARBITRARY AIRFOILMasayoshi Nakamura Aug. 1980 25 p refs(NAL-TR-602T) Avail: NTIS HC A02/MF A01

A method for obtaining shockless transonic flows past twodimensional airfoils is described. The methods of calculations oftransonic flows are roughly classified into two groups: the directmethod, which yields the transonic flows past given arbitraryairfoils: and the inverse method, which determines shapes ofairfoils. In the former method, tne shock waves normally existin the region of transonic flows, and some numerical methodsare already known. In the latter, transonic flows with given pressuredistribution are calculated, and several analytical methods alsoexist. The method described is a combination of the directmethod yield, the shockless transonic flows past airfoils whichare partially modified from a given arbitrary airfoil. If one putsan arbitrary airfoil into a region of free stream flows with acomparatively large free stream Mach number, the shock wavesgenerally exist. R.C.T.

N81-14984# National Aerospace Lab., Tokyo (Japan).AN INVESTIGATION OF SUPPORT-INTERFERENCEEFFECTSNoboru Hashimoto, Koichi Hozumi, Tadao Koyama, AkiraYoshizawa, and Takashi Matsuzaki Aug. 1980 28 p refs InENGLISH and JAPANESE(NAL-TR-622) Avail: NTIS HC A03/MF A01

Base pressure and pressure distribution on the sting surfacein the flow having a free stream Mach number of 7.1 and afree stream Reynolds number based on the unit length from0.2 x 10 to the 5th power to 2.0 to x 10 to the 5th power/cmwere measured. The oil flow observation on the sting surfacewas made at the same time. Avoiding the strong base pressurerise caused by the effect of strut, the sting flare corner effectwas investigated. The experimental results showed that the basepressure depends upon the Reynolds number and is affected bythe interaction of the base recirculating flow and the separatedflow around the sting flare corner. This effect of the sting flarecorner becomes smaller as the length of the sting increasesand the standard length of a sting which has a sufficiently minimaleffect on the base pressure was obtained. In order to predictthe base pressure of the sting mounted models, the correlationof the base pressure with local flow properties, immediatelypreceding the base, is discussed for those cases where there islittle effect from the sting flare and strut. T.M.

N81-14985# Aeronautical Research Inst. of Sweden. Stockholm.Structures Dept.THE VELOCITY INDUCED BY THE WAKE OF A WINDTURBINE IN A SHEAR LAYER. INCLUDING GROUNDEFFECT

Bo C. A. Johansson 17 Sep. 1980 51 p refs(Contract NE-5061-013)(FFA-TN-HU-2189-pt-3: ISSN-0081-5640: FFA-133) Avail:NTIS HC A04/MF A01

The turbine was approximated by a disk area of continuousdistributions of thrust and force parallel to the disk plane. Itswake was represented by a semi-infinite cylinder of distributedvorticity. A numerical example was calculated. The theory isbased upon assumptions strictly valid only for small perturbationsof the undisturbed flow. However, the results may have a widerrange of applicability. T.M.

N81-14986# Flow Research. Inc.. Los Angeles, Calif.DEVELOPMENT OF FINITE-VOLUME METHODS FORTHREE-DIMENSIONAL TRANSONIC FLOWSJohn E. Mercer. Wen-Huei Jou. David A. Caughey. AnthonyJameson, and David Nixon Aug. 1980 110 p refs(Contract N00014-78-C-0079)(AD-A090829: FLOW-RR-166) Avail: NTISHC A06/MF A01 CSCL 20/4

This report covers the Phase II progress in a two phaseeffort to develop the full potential finite volume algorithm fortransonic flow over wing-body configurations. The work in-cluded investigations of grid-generation schemes, extension ofthe wing-body code to more complex configurations, and theeffects of vortex wake modeling. The wing-body code was usedto analyze a computer designed military aircraft wing which hadbeen wind tunnel tested. Computed results agree quite well withthe experimental data. A second test case was also run for abusiness jet aircraft. Unfortunately, experimental data for thetest case were not available for comparison. GRA

N81-14987# National Transportation Safety Board. Washington,D. C. Bureau of Technology.BRIEFS OF ACCIDENTS INVOLVING COMMUTER AIRCARRIERS AND ON-DEMAND AIR TAXI OPERATIONS. U.S.GENERAL AVIATION 19785 Aug. 1980 193 p(PB81-101701: NTSB-AMM-80-11) Avail: NTISHC A09/MF A01 CSCL 01B

Included are 55 commuter air carrier and 216 on demandair taxi accident briefs. The brief format presents the facts,conditions, circumstances and probable cause(s) for each accident.Additional statistical information is tabulated by type of operation,injuries, aircraft weight, and causes(s) and related factor(s). T.M.

N81-14988# National Transportation Safety Board, Washington,D. C. Bureau of Accident Investigation.COMMUTER AIRLINE SAFETY Special Study. 1970 -197922 Jul. 1980 53 p refs(PB81-104267: NTSB-AAS-80-1) Avail: NTISHC A04/MF A01 CSCL 01 B

A review of the predominant safety issues which effect thecommuter airline industry and a review of the relationship ofthe Federal regulations to the commuter airlines are presented.The Safety Board developed the basis of the study from its1972 special study of air taxis, the Board's accident statistics,and accident investigation experience and from an extensive fieldsurvey. The operational maintenance, training, and regulatory areasof the industry are discussed and safety deficiencies are analyzed.A number of safety recommendations to the FAA designed toenhance the commuter airline industry are presented. T.M.

N81-14989*# Ohio Univ.. Athens. Avionics EngineeringCenter.DC-TO-DC POWER SUPPLY FOR LIGHT AIRCRAFT FLIGHTTESTINGStephen R. Yost Dec. 1980 7 p ref(Grant NGR-39-009-017)(NASA-CR-163850: TM-76) Avail: NTIS HC A02/MF A01CSCL 17G

The power supply unit was developed to serve as the powersource for a Loran-C receiver.The power supply can be connecteddirectly to the aircraft's electrical system, and is compatible with

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either 14 or 28 volt electrical systems. Design specificationsare presented for the unit along with a description of the circuitdesign. T.M.

N81-14991*# California Polytechnic State Univ.. San LuisObispo.FLIGHT EVALUATION OF THE TERMINAL GUIDANCESYSTEMDoral R. Sandlin 1981 65 p refs(Grant NsG-4022)(NASA-CR-163859) Avail: NTIS HC A04/MF A01 CSCL17G

The terminal guidance system (TGS) is avionic equipmentwhich gives guidance along a curved descending flight path toa landing. A Cessna 182 was used as the test aircraft and theTGS was installed and connected to the altimeter. DME. RMI.and gyro compass. Approaches were flown by three differentpilots. When the aircraft arrives at the termination point, it isset up on final approach for a landing. The TGS provides guidancefor curved descending approaches with guideslopes of 6 degwhich required, for experienced pilots, workloads that areapproximately the same as for an ILS. The glideslope is difficultto track within 1/2 n.m. of the VOR/DME station. The systempermits, for experienced pilots, satisfactory approaches with aturn radius as low as 1/2 n.m. and a glideslope of 6 deg. Turnangles have little relation to pilot workload for curved approaches.Pilot experience is a factor for curved approaches. Pilots withlow instrument time have difficulty flying steep approaches withsmall turn radius. Turbulence increases the pilot workload forcurved approaches. The TGS does not correct to a given flightpath over the ground nor does it adequately compensate forwind drift. E.D.K.

N81-14992# Deutsche Forschungs- und Versuchsanstalt flierLuft- und Raumfahrt. Brunswick (West Germany). AbteilungFlugzeugsteuerung und -Regelung.APPLICATEO TECHNIQUES FOR THE CONTROL OFAPPROACH TRAFFICAlbrecht Seyfried (Tech. Univ.. Brunswick), Manfred Schubert.and Uwe Voelckers (Tech. Univ.. Brunswick) Oct. 1979 31 prefs In GERMAN; ENGLISH summary Report will also beannounced as translation (ESA-TT-668)(DFVLR-Mitt-79-20) Avail: NTIS HC A02/MF A01

The achievement of a regular distributed aircraft arrival rateat the TM borders and the smooth integration of different flowsof traffic are the main objects of flow control in the approacharea. With respect to these goals some fundamental flow controlmeasures normally being applied in a selected near terminalarea were investigated by the analysis of real traffic recordingsas well as by controller interviews. The effects of certain flowcontrol principles on the entry and exit distribution and on thefurther evolution of traffic within the TMA are explained. Finallyit is discussed to which degree such different flow controltechniques should be considered in a future computer assistedATC system. Author

N81-14993*# Lockheed-Georgia Co.. Marietta.A SURVEY OF NEW TECHNOLOGY FOR COCKPIT APPLICA-TION TO 1990'S TRANSPORT AIRCRAFT SIMULATORSFinal Report. Jul. 1979 - Jan. 1980A. P. Holt. Jr.. D. 0. Noneaker. and L Walthour Dec. 1980118 p refs(Contract NAS1-15546)(NASA-CR-159330: LG81ER0074) Avail: NTISHC A06/MF A01 CSCL 01C

Two problems were investigated: inter-equipment datatransfer, both on board the aircraft and between air and ground:and crew equipment communication via the cockpit displays andcontrols. Inter-equipment data transfer is discussed in terms ofdata bus and data link requirements. Crew equipment communica-tion is discussed regarding the availability of CRT display systemsfor use in research simulators to represent flat panel displays ofthe future, and of software controllable touch panels. T.M.

N81-14994*# Lockheed-Georgia Co.. Marietta.ADVANCED FLIGHT DECK/CREW STATION SIMULATORFUNCTIONAL REQUIREMENTS Final Report. Oct. 1979 -Feb. 1980R. L. Wall. J. L. Tate, and M. J. Moss Dec. 1980 145 prefs(Contract NAS1-15546)(NASA-CR-159331: LG80ER0035) Avail: NTISHC A07/MF A01 CSCL 01C

This report documents a study of flight deck/crew systemresearch facility requirements for investigating issues involvedwith developing systems, and procedures for interfacing transportaircraft with air traffic control systems planned for 1985 to 2000.Crew system needs of NASA, the U.S. Air Force, and industrywere investigated and reported. A matrix of these is included,as are recommended functional requirements and design criteriafor simulation facilities in which to conduct this research. Methodsof exploiting the commonality and similarity in facilities areidentified, and plans for exploiting this in order to reduceimplementation costs and allow efficient transfer of experimentsfrom one facility to another are presented. Author

N81-14995# Oak Ridge Y-12 Plant. Tenn.F-111 WINDSCREEN MACHINING Final ReportH. L. Gerth and R. J. Brown 22 Sep. 1980 22 p refs(Contract W-7405-eng-26)(Y-2232) Avail: NTIS HC A02/MF A01

The feasibility of improving the optical image transmittedthrough a military aircraft windscreen by using single-pointdiamond turning is studied. Reduced warpage (waviness) of thewindscreen surfaces ensures that a more accurate optical imageis presented to the aircraft pilot. Machining the acrylic surfacewas accomplished with slightly impared image transmissibility.The use of this technique as a potential production process isdiscussed. DOE

N81-14996*# New Mexico Univ.. Albuquerque. TechnologyApplication CenterREMOTELY PILOTED VEHICLES. CITATIONS FROM THEINTERNATIONAL AEROSPACE ABSTRACTS DATA BASEProgress Report, 1974 - Jul. 1980Samuel C. Mauk Sep. 1980 59 p Supersedes NTIS/PS-79/0875/9 Sponsored in part by NASA and NTIS( N A S A - C R - 1 6 3 8 6 4 ; NTIS/PS-79/0875/9: PB80-815921)Avail: NTIS HC S30.00/MF $30.00 CSCL01C

These citations from the international literature cover variousaspects of remotely piloted vehicles. Included are articlesconcerning aircraft design, flight tests, aircraft control, costeffectiveness, automatic flight control, automatic pilots, and datalinks. Civil aviation applications are included, although militaryuses of remotely piloted vehicles are stressed. This updatedbibliography contains 224 citations. 43 of which are new additionsto the previous edition. GRA

N81-14997*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.SIMULATOR STUDY OF CONVENTIONAL GENERALAVIATION INSTRUMENT DISPLAYS IN PATH-FOLLOWINGTASKS WITH EMPHASIS ON PILOT-INDUCED OSCILLA-TIONSJames J. Adams Dec. 1980 55 p refs(NASA-TP-1776: L-13785) Avail: NTIS HC A04/MF A01CSCL 01D

A study of the use of conventional general aviation instrumentsby general aviation pilots in a six degree of freedom, fixed basesimulator was conducted. The tasks performed were tracking aVOR radial and making an ILS approach to landing. A specialfeature of the tests was that the sensitivity of the displacementindicating instruments (the RMI. CDI. and HSI) was keptconstant at values corresponding to 5 n. mi. and 1.25 n. mi.from the station. Both statistical and pilot model analyses ofthe data were made. The results show that performance in pathfollowing improved with increases in display sensitivity up tothe highest sensitivity tested. At this maximum test sensitivity,which corresponds to the sensitivity existing at 1.25 n. mi. forthe ILS glide slope transmitter, tracking accuracy was no better

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than it was at 5 n. mi. from the station and the pilot aircraftsystem exhibited a marked reduction in damping. In some cases,a pilot induced, long period unstable oscillation occurred. Author

N81-14998* Beam Engineering. Inc.. Sunnyvale. Calif.STATIC SOURCE LOCATIONS FOR FOUR NOZZLESMOUNTED ON A J 85 ENGINE Final ReportLeif E. Hoglund Jan. 1979 236 p refs(Contract NAS2-9399)(NASA-CR-152401) Avail: NASA. Ames Research CenterCSCL 21E

The test nozzles included a round 17.5 in. diameter variableflap ejector (VFE) nozzle, a round 'stovepipe' nozzle, and a104 tube suppressor nozzle operated both with and without anejector shroud. The velocities tested ranged from 600 to 1600fps at an approximate total temperature of 1400 R. The axialposition of the noise sources during static operation wasdetermined by jet velocity. Strouhal number, and direction ofpropagation. The velocity dependence was more evident for the104 tube suppressor nozzle than for the conical nozzles tested.The results for both the VFE conical nozzle and the stovepipeconical nozzle indicate source locations to be much closer tothe jet exit plane than expected. Corrections for near field effectswere found to differ slightly for each nozzle tested. The correctionspresented are simply the differences between the measurednear field levels and the required near field levels if spherics!spreading is assumed from source to far field. Author

N81-14999* National Aeronautics and Space Administration.Lewis Research Center. Cleveland, Ohio.CURVED CENTERLINE AIR INTAKE FOR A GAS TURBINEENGINE PatentWilliam C. Ruehr (GE. Cincinnati). James L Younghans (GE.Cincinnati), and Edwin B. Smilh. inventors (to NASA) (GE.Cincinnati) Issued 2 Sep. 1980 6 p Filed 14 May 1979Sponsored by NASA(NASA-Case-LEW-13201-1; US-Patent-4.220.171;US-Patent-Appl-SN-038980; US-Patent-Class-137-15.1:US-Patent-Class-181-214) Avail: US Patent and TrademarkOffice CSCL 21E

An inlet for a gas turbine engine was disposed about acurved centerline for the purpose of accepting intake air that isflowing at an angle to engine centerline and progressively turningthat intake airflow along a curved path into alignment with theengine. This curved inlet is intended for use in under the winglocations and similar regions where airflow direction is alteredby aerodynamic characteristics of the airplane. By curving theinlet, aerodynamic loss and acoustic generation and emissionare decreased.

Official Gazette of the U.S. Patent and Trademark Office

N81-150OO*# National Aeronautics and Space AdministrationHugh L. Dryden Flight Research Center, Edwards, Calif.FLIGHT EVALUATION OF A SIMPLIFIED GROSS THRUSTCALCULATION TECHNIQUE USING AN FIDO TURBOFANENGINE IN AN F 15 AIRPLANEFrank J. Kurtenbach and Frank W. Burcham. Jr. Jan. 198121 p refs(NASA-TP-1782: H-1118) Avail: NTIS HC A02/MF A01 CSCL21E

A simplified gross thrust calculation technique was evaluatedin flight tests on an F-15 aircraft using prototype F100-PW-100engines. The technique relies on afterburner duct pressuremeasurements and empirical corrections to an ideal one-dimensional analysis to determine thrust. In-flight gross thrustcalculated by the simplified method is compared to gross thrustcalculated by the engine manufacturer's gas generator model.The evaluation was conducted at Mach numbers from 0.6 to1.5 and at altitudes from 6000 meters to 13.700 meters. Theflight evaluation shows that the simplified gross thrust methodand the gas generator method agreed within plus or minus3 percent. The discrepancies between the data generally fellwithin an uncertainty band derived from instrumentation errorsand recording system resolution. A.R.H.

N81 15001*# Purdue Univ.. Lafayette. Ind. School ofMechanical Engineering.APPLICATION OF THE MNA DESIGN METHOD TO ANONLINEAR TURBOFAN ENGINE Final ReportGary Leininger Jan. 1981 107 p ref-;(Grant NsG-3171)(NASA-CR-163855) Avail: NTIS HC A06/MF A01 CSCL21E

Using nonlinear digital simulation as a representative modelof the dynamic operation of the QCSEE turbofan engine, a feedbackcontrol system is designed by variable frequency design tech-niques. Transfer functions are generated for each of five powerlevel settings covering the range of operation from approachpower to full throttle (62.5% to 100% full power). These transferfunctions are then used by an interactive control system designsynthesis program to provide a closed loop feedback controlusing the multivariable Nyquist array and extensions to multivari-able Bode diagrams and Nichols charts. A.R.H.

N81-15003*# Spectron Development Labs.. Inc.. Costa Mesa.Calif.FUEL INJECTOR CHARACTERIZATION STUDIES FinalReportMichael J. Houser and William D. Bachalo Oct. 1980 54 prefs(Contract NAS3-21288)(NASA-CR-165200; SDL-80-2122-13F) Avail: NTISHC A04/MF A01 CSCL 21E

The atomization of several general aviation piston enginemanifold port fuel injectors was investigated The injectors wereinstalled in a test rig and operated under simulated conditions.Laser interferometric techniques were used to optically probethe spray droplet fields for droplet size and velocity at numerousspatial locations throughout the field. R.C.T.

N81-150O4*# General Electric Co.. Cincinnati. Ohio. AircraftEngine GroupAERODYNAMIC STABILITY ANALYSIS OF NASA J85-13/PLANAR PRESSURE PULSE GENERATOR INSTALLATIONK Chung. W. M. Hosny. and W. G Steenken Nov. 1980168 p refs(Contract NAS3-21259)(NASA-CR-165141; R80AEG429) Avail: NTISHC A08/MF A01 CSCL 21E

A digital computer simulation model for the J85-13/PlanarPressure Pulse Generator (P3 G) test installation was developedby modifying an existing General Electric compression systemmodel. This modification included the incorporation of a novelmethod for describing the unsteady blade lift force This approachsignificantly enhanced the capability of the model to handleunsteady flows. In addition, the frequency response characteristicsof the J85-13/P3G test installation were analyzed in support ofselecting instrumentation locations to avoid standing wave nodeswithin the test apparatus and thus, low signal levels. The feasibilityof employing explicit analytical expression for surge predictionwas also studied. J.M.S.

N81-150O5*# General Electric Co.. Cincinnati. Ohio. AircraftEngine Group.TF34 ENGINE COMPRESSION SYSTEM COMPUTERSTUDYW. M. Hosny and W. G. Steenken Jun. 1979 93 p refs(Contract NAS3-20599)(NASA-CR-159889: R78AEG612) Avail: NTISHC A05/MF A01 CSCL 21E

The stability of the fan and the compressor componentswas examined individually using linearized and time dependent,one dimensional stability analysis techniques. The stability ofthe fan core integrated compression system was investigatedusing a two dimensional compression system model. Theanalytical equations on which this model was based satisfiedthe mass, axial momentum, radial momentum, and energyconservation equations for flow through a finite control volume.The results gave an accurate simulation of the flow through thecompression system. The speed lines of the components were

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reproduced: the points of instability were accurately predicted:the locations where the instability was initiated in the fan andthe core were indicated: and the variation of the bypass ratioduring flow throttling was calculated. The validity of theanalytical techniques was then established by comparing theseresults with test data and with results obtained from the steadystate cycle deck. J.M.S.

N81-15OO6*# Pratt and Whitney Aircraft Group. East Hartford.Conn. Commercial Products Div.COST/BENEFIT ANALYSIS OF ADVANCED MATERIALSTECHNOLOGIES FOR FUTURE AIRCRAFT TURBINEENGINES Final ReportG. E. Stephens Aug. 1980 49 p refs(Contract NAS3-20072)(NASA-CR-165225: PWA-5755) Avail: NTISHC A03/MF A01 CSCL 21E

The materials technologies studied included thermal barriercoatings for turbine airfoils, turbine disks, cases, turbine vanesand engine and nacelle composite materials. The cost/benefit ofeach technology was determined in terms of Relative Value definedas change in return on investment times probability of successdivided by development cost. A recommended final ranking oftechnologies was based primarily on consideration of RelativeValues with secondary consideration given to changes in othereconomic parameters. Technologies showing the most promisingcost/benefits were thermal barrier coated temperature nacelle/engine system composites. T.M.

N81-150O7# Texas Univ. at Arlington.. Dept. of AerospaceEngineering.A PURE DIRECT FORCE/MOMENT CONTROL FORCOAXIAL COUNTERROTATING ROTORSAspi Rustom Wadia (AiResearch Mfg. Co.. Phoenix. Ariz.) andJack E. Fairchild [1980] 19 p refsAvail: NTIS HC A02/MF A01

A simple first harmonic analysis using Fourier series ispresented for the control of rigid coaxial and counterrotatinghelicopter rotors in hover. It it shown that by a particularcombination of cyclic controls on each rotor, pure moments orforces can be generated in any direction. Such controls couldgive the helicopter maneuvering capabilities not possible inconventional machines. An elementary cockpit control configura-tion is suggested to implement the control strategy. E.D.K.

N81-15009$ Royal Aircraft Establishment. Farnborough(England). Structures Dept.THE RESONANCE FREQUENCIES OF VENTILATED WINDTUNNELS0. G. Ma bey London Apr. 1978 52 p refs SupersedesRAE-TR-78038: ARC-37974(ARC-R/M-3841: BR73233: RAE-TR-78038: ARC-37974)Avail: NTIS HC A04/MF A01: HMSO £8 PHI

Experiments suggest that the theory widely used to predictthe transverse resonance frequencies in slotted tunnels is in errorin the Mach number range from 0 to 0.5. One reason for theerror is that the theory is based on an unrepresentative wallboundary condition. Moreover, the theory implies that the plenumchamber surrounding the working section is large, whereas theplenum chamber depth is generally less than twice the tunnelheight. An improved theory was developed, which shows thatthe resonance frequencies of ventilated tunnels are influencedby the depth of the plenum chamber for Mach numbers up toabout M = 0.6. Although the theory is approximate, it agreeswell with experiments for slotted and perforated walls (with bothnormal and 60 deg inclined holes). The results are consistentwith other experiments which show that plenum chamber designcan influence the flow unsteadiness within the working sectionof a ventilated tunnel. Author

N81-15072$ Societe Nationale Industrielle Aerospatiale,Suresnes (France). Lab. Centrale.THE RESISTANCE OF TANK PROTECTIVE MEASURES TOMICROORGANISMS [RESISTANCE DES PROTECTIONSDE FONDS DE RESERVOIRS AUX MICROORGANISMES]

G. Dallemagne Paris 16 Sep. 1980 18 p refs In FRENCHPresented at 4eme Journees du Vieillissement des Polymeres,Station de Bandol, 19 Sep. 1980(SNIAS-801-551-107) Avail: NTIS HC A02/MF A01

Various paints, pigments, and varnishes were studied todetermine their effectiveness in protecting JPI/H20 againstbiocontamination by Cladiosporium resinae. In order of decreasingresistance, they were found to be: (1) PU: a varnish polymerizedat 60 C and promers inhibited by ZnCr04 and SrCr04: (2) acured epoxy/amine primer, inhibited by BaCrO4: and(3) epoxide/amide and epoxide/amme-amide primers inhibitedby SrCr04. Of the systems examined, it is advisable not to useNBR varnish, with and without inhibitors, and epoxide/amine-amide primers inhibited by BaCr04 in biodeteriorating milieu.

Transl. by A.R.H.

N81-15148# Mason and Hanger-Silas Mason Co., Inc.. Amarillo.Tex. Development Div.TOOL FORCE EVALUATION OF LATHE MACHINED HIGHEXPLOSIVESGary L. Flowers Apr. 1980 44 p(Contract DE-AC04-76DP-00487)(MHSMP-80-20: Endeavor-302) Avail: NTISHC A03/MF A01

A procedure to determine the effects of machining propertiesupon tool forces encountered during lathe machining of highexplosives is evaluated. Transducers fit between the tool holderand the tool post and interface to existing signal conditioners.All forces on the cutter were evaluated during machining oftwo types of high explosives at four cutter radii, four feed rates,three depths of cut. and two cutting speeds Findings indicatethat the transducer design is inadequate to allow accurate forcevector separation at all reasonable attack angles. Problemsconcerning instrument drift, tool chatter, and detection levelsate also found. M G

N81-15156# Toronto Univ.. Downsview (Ontario). Inst. forAerospace Studies.HEAVE INSTABILITIES OF AMPHIBIOUS AIR CUSHIONSUSPENSION SYSTEMSM. J. Hinchey Nov. 1980 135 p refs Sponsored by TransportCanada Research and Development Centre and National ResearchCouncil of Canada(UTIAS-246: ISSN-0082-5255) Avail: NTISHC A07/MF A01

Attempts to ascertain the accuracy with which analyticalmodels can be used to predict the onset of heave instabilitiesare described with emphasis on relatively simple configurationsin which important effects are uncoupled. For the basic elementof multicell systems, even relatively short supply ducting canhave a very large effect, especially at low flows or hover-gapswhere the duct-cushion system tends to behave as a Helmholtzresonator. For loop and segment systems, it is concluded thatduct effects would be small. Internal flow effects associatedwith jets and vortices within the basic cushion volume are shownto be relatively unimportant at practical flow rates, althoughthey are important at very high flow rates. Nonlinear phenomena,and procedures for controlling or quenching limit cycle amplitudesare explored. Suggestions for future work are included. A.R.H.

N81-15310# Von Karman Inst. for Fluid Dynamics. Rhode-Saint-Genese (Belgium). Dept. of Computational Fluid Dynamics.COMPUTATIONAL FLUID DYNAMICS. VOLUME 21980 380 p refs Lecture held in Rhode-Saint-Genese. Belgium.24-28 Mar. 1980 2 Vol.(VKI-LS-1980-5-Vol-2) Avail: NTIS HC A17/MF A01

Several aspects of computational fluid dynamics are discussed.Theoretical methods are developed for computing the aerodynamicflow of aircraft configurations.

N81-15311# Jenkins (Gwilym) and Partners Ltd.. Lancaster(England).AN ECONOMIC AND VERSATILE PANEL METHOD FORAIRCRAFT AND AIRCRAFT/STORE CONFIGURATIONS.

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AN OUTLINE OF THE PRINCIPAL FEATURES OF THEMATHEMATICAL MODELING AND NUMERICAL IMPLE-MENTATION OF THE BRITISH AEROSPACE (WARTON)MK II PANEL METHODW. G. Semple In Von Kacman Inst. for Fluid Dyn. ComputationalFluid Dyn.. Vol. 2 1980 70 p refs Prepared in cooperationwith British Aerospace Aircraft Group. Preston, England

Avail: NTIS HC A17/MF A01The principal features of the mathematical modeling and

numerical implication of the MK 11 panel method are outlined.The geometric structure, conventions and terminology of MK11are given. The method of solution of the linear equations forthe source and doublet weights are described. A brief review ofresults from the method is given and the possible avenues offuture development are summarized. R.CT.

N81-15313*# National Aeronautics and Space Administration.Ames Research Center. Moffett Field. Calif.VORTEX METHODS FOR TWO- AND THREE-DIMENSIONALFLOW SIMULATIONSA. Leonard In Von Karman Inst. for Fluid Dyn. ComputationalFluid Dyn.. Vol. 2 1980 52 p refs

Avail: NTIS HC A17/MF A01The point vortex and vortex blob methods for two dimensional

flows are presented. Several results are discussed concerningthe numerical analysis of the latter scheme, e.g.. the preservationof globally conserved quantities and the analysis of the spatialdiscretization error resulting from the convection of fixed blobsof vorticity. An application to the two dimensional mixing layeris briefly described. The contour dynamics method is alsodiscussed. The simulation of three dimensional flows with vortexmethods is discussed. A natural way to represent the vorticityis in the form of closed tubes of filaments of vorticity, althoughother schemes are examined. Applications to aircraft trailingvortices and to a turbulent spot in a laminar boundary layer arepresented. Hybrid schemes that use an Eulerian mesh to solvethe Poisson equation for the velocity field are discussed. Thegoal of these schemes is to avoid the high cost of the Biot-Savartintegration if many vortex elements are used while enjoying mostof the advantages of pure Lagrangian schemes. R.CT.

N81-15362 Texas A&M Univ.. College Station.PROBABILISTIC ANALYSIS OF FOUNDATION FORCES FORA CLASS OF UNBALANCED ROTATING MACHINESPh.D. ThesisLola Boyce 1980 105 pAvail: Univ. Microfilms Order No. 8101577

The rotor-housing is modeled as a three degree-of-freedomsystem wherein the principal modes of vibration are a verticaltranslation in the direction of the machine supports and a rollingand pitching motion of the rotor. The equations of motion forthe system are derived using analytical methods, solved, andrelated to the foundation force. For a selected machine class,all parameters are constant except for rotor mass eccentricity.the distance from the center of mass of the rotating mass tothe bearing axis. The deterministic analysis requires the selectionof some representative value of eccentricity from the data availablefor a number of rotors. The corresponding foundation force iscalculated. No measure of the error associated with the foundationforce is available. The probabilistic analysis requires the calculationof the mean value of the foundation force and includes somemeasure for its error. The classical probabilistic method accountsfor foundation force error by employing the propagation of errorsformula to calculate variance. Dissert. Abstr.

N81-15397*# National Aeronautics and Space Administration.Langley Research Center. Hampton. Va.EFFECTS OF ANGLE OF ATTACK AND VENTRAL FIN ONTRANSONIC FLUTTER CHARACTERISTICS OF AN ARROW-WING CONFIGURATIONRobert V. Doggett and Rodney A. Ricketts Dec. 1980 29 p(NASA-TM-81914: L-14114) Avail: NTIS HC A03/MF A01CSCL 20K

Experimental transonic flutter results are presented for asimplified 1/50 size, aspect ratio 1.77. wind tunnel model ofan arrow wing design Flutter results are presented for twoconfigurations: namely, one with and one without a ventral finmounted at the 0.694 semispan station. Results are presentedfor both configurations trimmed to zero lift and in a lifting conditionat angles of attack up to 4 deg. The results show that theflutter characteristics of both configurations are similar to thoseusually observed. Increasing angle of attack reduces the flutterdynamic pressure by a small amount (about 13 percent maximum)for both configurations. The addition of the fin to the basicwing increases the flutter dynamic pressure. Calculated resultsfor both configurations in the nonlifting condition obtained byusing subsonic doublet lattice unsteady aerodynamic theorycorrelate reasonably well with the experimental results. Calculatedresults for the basic wing obtained by using subsonic kernalfunction unsteady aerodynamic theory did not agree as well withthe experimental data Author

N81-15401# Instituut TNO voor Werktuigkundige Constructies.Delft (Netherlands).EXPERIMENTAL ANALYSIS AND METHODS TO DETER-MINE THE DYNAMIC BEHAVIOR OF PROPULSIONSHAFTING SYSTEMSL. J. Wevers In Ned. Akoestisch Genootschap Vibration Tech.Jan. 1980 p 13-35 refs In DUTCH: ENGLISH summary

Avail: NTIS HC A03/Mt- A01The dynamic bending properties of propeller shaftings were

investigated. Measurements were taken at a full size laboratoryfacility and onboard ships. The aim of the measurements wasto verify the results of a numerical calculation method with afinite element program developed to face lateral vibrationproblems in an early stage of the design of a ship's propulsionsystem. R.C.T.

N81-15414# Westinghouse Electric Corp., Concordville, Pa.Combustion Turbine Systems Div.COMPRESSOR CONFIGURATION AND DESIGN OPTIMIZA-TION FOR THE HIGH RELIABILITY GAS TURBINE FinalReportR. E. Strong Sep. 1980 128 p refs(Contract DE-AC03-79ET-15332)(OOE/ET-15332/T1) Avail. NTIS HC A07/MF A01

An advanced compressor for use in the high reliabilitycombustion turbine engine was investigated. Advanced designconcepts based on low aspect ratio aircraft engine compressortechnology were utilized to define three compressor configurationswith 11. 13 and 15 stages. The results were applied tocompressors with 14:1 pressure ratio. 800 Ibs/sec (360 kg/sec)airflow and operating at 3600 rpm to match the requirementsof heavy duty power generation combustion turbine engines.Typical, front, middle and last stages of these three compressorswere studied to evaluate their aerodynamic and mechanicalfeasibility and to determine the influence of the number of stages,and stage loadings on their overall efficiency. The 11 stagecompressor was selected for further mechanical analysis to verifyits structural constraints and define in greater detail its mechani-cal configuration. Cost of this compressor was estimated forcomparison with the present 19 stage high reliability referencecompressor derived from the Westinghouse W-501 engine.

R.C.T.

N81-15467# Stuttgart Univ. (West Germany). Inst. fuer Statikund Dynamik.ROTOR MODEL FOR VERIFICATION OF COMPUTATIONMETHODS [ROTORMODELL ZUR VERIFIZIERUNG VONRECHENVERFAHREN]J. H. Argyris. W. Aicher, F. Karl. W. Kuemmerle. and M. Mueller1979 58 p refs In GERMAN: ENGLISH summary(Contract BMFT-ET-4086-A)(ISD-262: ISSN-0170-6071) Avail: NTIS HC A04/MF A01

In order to prove the quality of idealization and the validityof computation for windmills, a driven model of a windmill witha 7.4 m diameter rotor was constructed. New data acquisitionand data transmission systems with 16 channels and digitization

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in the rotating system were developed and tested. The dynamicresponse of the rotor blades to the cyclic loading of gravity wastaken to compare measurements and computations. For themeasurements and evaluation which were performed by ameasurement system and a computer, the necessary softwarewas built. T.M.

N81-15579*# National Aeronautics and Space Administration,Washington. D. C.THE ANNOYANCE CAUSED BY NOISE AROUND AIRPORTSFinal ReportJosse Jul. 1980 114 p refs Transl. into ENGLISH of "laGene causee par le Bruit Autour des Aeroports" Rept.D.G.R.S.T/C.S.T.B.-63-FR-138 Centre Sci. et Tech. du Batiment.Paris. 1 Mar. 1968 p 1-219 Transl. by Scientific TranslationService, Santa Barbara. Calif.(Contract NASw-3198)(NASA-TM-75784; DGRST/CSTB-63-FR-1 38) Avail: NTISHC A06/MF A01 CSCL 13B

A comprehensive study of noise around selected airports inFrance was performed. By use of questionnaires, the degree ofannoyance caused by aircraft noise was determined. Threeapproaches used in the study were: (1) analytical study on theinfluence of noise on sleep: (2) sociological study on thesatisfaction of occupants of buildings which conform to lawswhich are supposed to guarantee sufficient comfort; and(3) statistical study of correlations between external noises andpsychological and pathological disturbances in residences. E.O.K.

N81 15580# Toronto Univ., Downsview (Ontario). Inst. forAerospace Studies.AIRCRAFT ANNOYANCE EVALUATIONS USING FIELDAND LABORATORY SIMULATION TECHNIQUESG. W Johnston and A. A. Haasz Dec. 1980 60 p refsSponsored in part by Transport Canada(UTIAS-248: ISSN-0082-5255) Avail: NTISHC A04/MF A01

A series of aircraft noise annoyance evaluation tests wereperformed under controlled conditions in a laboratory. Jurorsdrawn from nominal 30-35 NEF zones were exposed to aircraftnoise events previously recorded near their homes in the vicinityof the Toronto International and Oshawa General Aviation Airports.Comparison of test results indicates that under optimum simulationconditions both Toronto and Oshawa observers consistently ratethe International Airport noise exposure as considerably moredisturbing/ annoying than that at the General Aviation Airportsites. The laboratory test results were also compared withconventional field interview annoyance data obtained for the samegroup of jurors in a previous study conducted by McMasterUniversity. Author

N81-16648*# New Mexico Univ.. Albuquerque. TechnologyApplication Center.LIGHTNING. CITATIONS FROM THE INTERNATIONALAEROSPACE ABSTRACTS DATA BASE Progress Report,1974 - Jul. 1980Samuel C. Mauk Sep. 1980 73 p Supersedes NTIS/PS-79/0832/0 Sponsored in part by NASA and NTIS(NASA-CR-163857: PB80-815947) Copyright. Avail: NTISHC S30.00/MF $30.00 CSCL 048

These citations from the international literature concernvarious aspects of lightning. Articles covering aircraft hazards,aircraft safety, radio meteorology, circuit protection, electro-magnetic pulses, and electromagnetic radiation are included.Articles concerning atmospheric electricity and thunderstorms arestressed. This updated bibliography contains 304 citations, 95of which are new additions to be previous edition. GRA

N81-15649*# New Mexico Univ., Albuquerque. TechnologyApplication Center.CLEAN AIR TURBULENCE. CITATIONS FROM THEINTERNATIONAL AEROSPACE ABSTRACTS DATA BASEProgress Report. 1974 - Jul. 1980Samuel C. Mauk Sep. 1980 61 p Supersedes NTIS/PS-79/0858/5 Sponsored by NASA and NTIS

(NASA-CR-163863. PB80-815889; NTIS/PS-79/0858/5)Avail: NTIS HC S30.00/MF $30.00 CSCL 04B

These citations from the international literature describe allaspects of clear air turbulence (CAT). Articles covering researchand analysis, theories and experiments, detection and measure-ment equipment, simulation modeling, and CAT accidents involvingaircraft are included. This updated bibliography contains237 citations. 116 of which are new additions to the previousedition. GRA

N81-16702*# Duke Univ.. Durham. N. C. Dept. of ComputerSciences.VALIDATION METHODS RESEARCH FOR FAULT-TOLERANT AVIONICS AND CONTROL SYSTEMS SUB-WORKING GROUP MEETING. CARE 3 PEER REVIEWKishor S. Trivedi. ed. and James B. Clary, ed. (Research TriangleInst.. Research Triangle Park. N.C.) Dec. 1980 30 p refsMeeting held at Research Triangle Park. N.C.. 15-16 Sep. 1980(Grant NAG 1-70)(NASA-CP-2167: L-14215) Avail: NTIS HC A03/MF A01CSCL 12A

A computer aided reliability estimation procedure (CARE 3).developed to model the behavior of ultrareliable systems requiredby flight-critical avionics and control systems, is evaluated. Themathematical models, numerical method, and fault-tolerantarchitecture modeling requirements are examined, and the testingand characterization procedures are discussed. Recommendationsaimed at enhancing CARE 3 are presented: in particular, theneed tor a better exposition of the method and the user interfaceis emphasized. M.G.

N81-16729| Computer Sciences Corp.. Orlando. Fla.COMPUTER GENERATED IMAGERY (CGI) CURRENTTECHNOLOGY AND COST MEASURES FEASIBILITY STUDYFinal Technical Report. 22 Apr. - 26 Sep. 1980Leonard T. Suminski, Jr. and Paul H. Hulin 26 Sep. 1980189 p refs(Contract N61339-79-D-0008)(AD-A091636: CSC/TR-80/6008: PM-TRADE-RE-0012) Avail.NTIS HC A09/MF A01 CSCL 09/2

The primary purpose of this report is to determine thefeasibility of developing a cost/performance, cost estimating modelfor CGI visual systems. In doing so. vendor surveys were madeand an analysis of current and future technology/techniques wasconducted. The report makes recommendations for some costingefforts to be conducted by PMTRADE. along with recommenda-tions for other efforts. GRA

N81-15768*# National Aeronautics and Space Administration.Lewis Research Center. Cleveland. Ohio.ANALYSIS OF PRESSURE SPECTRA MEASUREMENTS INA DUCTED COMBUSTION SYSTEM Ph.D. Thesis - ToledoUniv.Jeffrey Hilton Miles Nov. 1980 138 p refs(NASA-TM-81583: E-558) Avail. NTIS HC A07/MF A01 CSCL20A

Combustion noise propagation in an operating ducted liquidfuel combustion system is studied in relation to the developmentof combustion noise prediction and suppression techniques. Thepresence of combustor emissions in the duct is proposed as theprimary mechanism producing the attenuation and dispersion ofcombustion noise propagating in an operating liquid fuelcombustion system. First, a complex mathematical model forcalculating attenuation and dispersion taking into account masstransfer, heat transfer, and viscosity effects due to the presenceof liquid fuel droplets or solid soot particles is discussed. Next,a simpler single parameter model for calculating pressureauto-spectra and cross-spectra which takes into accountdispersion and attenuation due to heat transfer between solidsoot particles and air is developed. Then, auto-spectra andcross-spectra obtained from internal pressure measurements ina combustion system consisting of a J-47 combustor can, aspool piece, and a long duct are presented. Last, analytical resultsobtained with the single parameter model are compared with

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the experimental measurements. The single parameter modelresults are shown to be in excellent agreement with themeasurements. J.M.S.

N81-15769*# Pratt and Whitney Aircraft Group. East Hartford.Conn. Commercial Products Div.IMPROVED METHODS FOR FAN SOUND FIELD DETER-MINATIOND. E. Cicon. T. G. Sofrin. and D. C. Mathews Jan. 1981 180 prefs(Contract NAS3-21391)(NASA-CR-165188: PWA-5635-43) Avail: NTISHC A09/MF A01 CSCL 20A

Several methods for determining acoustic mode structure inaircraft turbofan engines using wall microphone data were studied.A method for reducing data was devised and implemented whichmakes the definition of discrete coherent sound fields measuredin the presence of engine speed fluctuation more accurate. Forthe analytical methods, algorithms were developed to define thedominant circumferential modes from full and partial circumferen-tial arrays of microphones. Axial arrays were explored to definemode structure as a function of cutoff ratio, and the use ofdata taken at several constant speeds was also evaluated in anattempt to reduce instrumentation requirements. Sensitivities ofthe various methods to microphone density, array size andmeasurement error were evaluated and results of these studiesshowed these new methods to be impractical. The data reductionmethod used to reduce the effects of engine speed variationconsisted of an electronic circuit which windowed the data sothat signal enhancement could occur only when the speed waswithin a narrow range. T.M.

N81-16819*# Institut Franco-Allemand de Recherches. St Louis(France).APPLICATION OF OPTICAL METHODS TO THE STUDY OFJET NOISE AND TURBULENCE [APPLICATION DESMETHODES OPTIQUES, EN PARTICULAR A L'ETUDE DELA TURBULENCE ET DU BRUIT DES JETS]P. G. Sava and J. Haertig 1 Aug. 1980 16 p refs InFRENCH Presented at Journees sur les Methodes Optiques ala Mecanique des Fluides, Orsay, France. 26-27 Nov. 1979(ISL-CO-201/80) Avail: NTIS HC A02/MF A01

Optical methods are generally applied in fluid mechaics foreither visualization or measurement. The use of a laser anemometerto study flow velocity in a jet and its relaton to the sound

• radiated is described. The same acoustic emission phenomenonis also measued by combining the signals from four Schlierensystems with that from an interferometer. The use of an opticalFourier transformation approach with real time analysis todetermine the spatio-temporal structure of a field of mass volumesuch as a waveguide or free jet is also examined.

Transl. by A.R.H.

147

SUBJECT INDEXAERONAUTICAL ENGINEERING/M Continuing Bibliography (Suppl. 134)

Typical Subject Index Listing

APRIL 1981

IIUUHSrDe*elopient of advanced interceptor sabstractaral

•aterial —- graphite epoxy missile stroctnres-[AD-A090127] 181-11116

TITU REPORTNUMBER

The title is used to provide a description of the subject matter. When the title isinsufficiently descriptive of the document content, a title extension is added,separated from the title by three hyphens. The NASA or AIAA accession numberis included in each entry to assist the user in locating the abstract in the abstractsection of this supplement. If applicable, a report number is also included as anaid in identifying the document.

A-6 AIRCRAFTCirculation Control iing /CCB/ flight tests

181-194691-300 AIRCRAFT

Stress measurements on landing gear for the AirbusA-300 B2

A81-19299ABLATIVE HATBRIALS

Captive carry and free flight rain erosionconsiderations for reinforced ablativeflnorocarbon radome materials

A81-17U53iCCIDBlT PBEVEITIOI

Helicopter alarms - The use of ALAT incident andaccident record cards

A81-16689ACOUSTIC ATTBBOATIOH

Analysis of pressure spectra measurements in aducted combustion systen[NASA-TH-81583] H81-15768

ACOUSTIC DDCTSSound radiation from a finite length unflanged

circular duct vith uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712&CODSTIC BHISSIOH

Application of optical methods to the study of jetnoise and turbulence[ISL-CO-201/80] H81-15819

ACOUSTIC HEASOBEHEITSImproved methods for fan sound field determination

[HASA-CR-165188] 1181-15769ACODSTIC PROPAGATION

Propagation of three-dimensional acousticperturbations in channels of variablecross-sectional area at frequencies close tocutoff frequency

A81-19338The sonic boom from an aircraft flying along an

arbitrary path in a stratified atmosphere in thepresence of a three-component vind

A81-19636ACOUSTIC PEOPEBTIES

Sound radiation fron a finite length unflangedcircular duct vith uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712

ACOUSTICSThe Dalembertometer

[ISL-CO-220/79] H81-14292ADAPTIVE COHTHOl

Further investigations of adaptive-wall wind tunnels[AD-A091774] H81-13977

ADHESIVE BOHDIHGAutomatization of the adhesion process for

supporting airframe parts in light contour systemsA81-19297

Surface finishing[HASA-CASE-SSC-12631-3] H81-14077

AEEIAL PHOTOGRAPH!Aerial surveying of small areas from a small

remotely controlled droneA81-17525

Autonomous navigation using passively sensedterrain images

A81-17977ABROACOOSIICS

Hoise and noise abatement in fans and blowers: Areview[DFVLR-FB-80-16] H81-14796

Analysis of pressure spectra measurements in aducted combustion system[HASA-Tn-81583] H81-15768

AEBODIHAHIC CHARACTERISTICSConcorde aerodynamics and associated systems

development BookA81-16718

The method of superelenents in the dynamics ofcomplex structures

A81-16969Optimum selection of main parameters for the

reverse design of a supersonic military aircraftA81-17047

Aerodynamic design of a ducted propeller -Optimization of efficiency

A81-17146Variational principles and generalized variational

principles for the hybrid aerodynamic problem ofairfoil cascades on an arbitrary stream sheet ofrevolution

A81-17741Aerodynamic calculations and design of snbcritical

aerofoilsA81-17804

An aerodynamic design method for transonic axialflow compressor stage

A81-17805Characteristics of the velocity field near a

wing-body combination located at an angle ofattack to an oncoming supersonic flow

A81-19337Drag redaction through formation flight[DGLB PAPEB 80-106] A81-19393

Experimental investigation of a right angle wingwith partially separated flow with and withoutground effects[DGLB PAPEB 80-111] A81-19397

Conditions of generation and methods of dampingthe inlet vortex of a turbojet engine

A81-19442Nonlinear aerodynamic characteristics of a thin

airfoil of arbitrary plane configuration481-19629

Rotary balance data for a single-engineagricultural airplane configuration for anangle-of-attack range of 8 deg to 90 deg[HASA-CE-3311] H81-13923

Effects of nonlinearities on wing store flutter[HBB-FE-17/S/POB/27] H81-13974

A-1

AEEODIHAHIC COEFFICIEBTS SUBJECT IID8I

Experimental aerodynaaic characteristics of two7/STOL fighter/attack aircraft configurations atBach numbers from 0.1 to 1.4[BASA-TH-81234] H81-14981

Curved centerline air intake for a gas turbineengine[BASA-CASE-LEB-13201-1] B81-14999

ABBODIBAHIC COEFPICIEITSMind-tunnel test of an articulated helicopter

rotor model vith several tip shapes[BASA-TB-80080] H81-13918

AEBODTSAHIC COBFIGOBAIIORSSome aspects of optimizing the aerodynanics of

turbine stagesA81-19325

Fighters for the 1990sA81-19497

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 2: User's manual[HASA-CR-3352] B81-13920

Computational aerodynaaic design tools andtechniques used at fighter developnent[HBB-FE-122/S/POB/13] B81-13950

Laminar-airfoils for transport aircraft[DFVLR-liITT-80-07] B81-13952

Lou-speed wind-tunnel tests of two weathercockingsensors[HSBL-0171-TB] B81-14575

An investigation into grid patching techniquesB81-14708

Grid generation for general three-dimensionalconfigurations

B81-14714A system for aerodynamic design and analysis of

supersonic aircraft. Fart 1: Generaldescription and theoretical development[SASA-CR-3351 ] B81-14970

A system for aerodynamic design and analysis ofsupersonic* aircraft. Fart 3: Computer programdescription[BASA-CB-3353] B81-14971

Leading-edge deflection optimization for a highlyswept arrow wing configuration[8ASA-1P-1777] N81-14974

An investigation of support-interference effects[BAL-TB-622] S81-14984

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] B81-14986

AEBODTBABIC DRAGCalculation of the lift dependent drag polar of

cambered fighter plane configurations withdeflected maneuver flaps in the subsonic regionby Beans of a modified procedure according toLamar[DGLB PAPEB 80-109] A81-19395

Drag estimations for stream-line and cylindricalcontour distortions on aircraft fuselages andtrain cars[DGLB PAPEB 80-116] A81-19399

The determination of the induced drag on slimwings with high lift systems in the transonicregion[BBB-FE122] A81-19400

Thin minimum-drag airfoils481-19630

AERODIBAHIC FORCESClear air turbulence: Historical comments

B81-14562A system for aerodynamic design and analysis of

supersonic aircraft. Part 1: Generaldescription and theoretical development[HASA-CB-3351] H81-14970

ABBODTBAHIC IBIEBFBBEBCBA wall interference analysis in wind tunnels

A81-17472ABBODISAHIC LOADS

Survey of lorkshops on Heteorological andEnvironmental Inputs to Aviation Systems

H81-14556Transonic wind tunnel tests on an oscillating wing

with external store. Part 4: The wing withnnderwing: Store[AD-A077370] B81-14969

The velocity induced by the wake of a wind turbinein a shear layer, including ground effect[FFA-TB-HO-2189-PT-3] B81-14985

AERODIBASIC BOISEExhaust noise in flight: The role of acoustic

installation effects[PBH-90029] B81-14793

Static source locations for four nozzles aoantedon a J-85 engine[HASi-CB-152401] B81-14998

Carved centerline air intake for a gas turbineengine[BASA-CASE-LEi-13201-1 ] B81-14999

ABRODIBAHIC STIBILIItThe effect of aerodynamic coupling on the dynamics

of aircraft in fast rolling motionA81-17471

Practical aerodynaaics of the helicopter S1-6ARussian book

481-18600A contribution to stabilization of flight vehicle

parachute systems[ DFVLH-BITT-80-05] B81-13926

Active flutter suppression on an P-4P aircraftwith external stores using already existingcontrol surfaces[BBB-FE-17/S/POB/24] B81-13972

Aerodynamic stability analysis of BASAJ85-13/planar pressure pulse generatorinstallation[HASA-CB-165141] B81-15004

TF34 engine compression system computer studysimulation of flow stability[HASA-CB-159889] B81-15005

ABRODIBABIC ST1LUHGA status report on BASA general aviation

stall/spin flight testingA81-19471

Bodel vibrations beyond low-speed stallA81-19552

Aerodynamic side-force alleviator means[BASA-CASE-LAH-12326-1] H81-14968

Supersonic stall flutter of high speed fans intnrbofan engines•HASA-TH-81613] B81-14978

AEBODIIABICSSteady flow past a rectangular wing with

circulation that is variable along the spanA81-16551

Review of theoretical and experimental results onthree dimensional turbulent wakes and boundarylayers[OHERA-ST-1980-4] B81-13930

Development of high-rtemperatnre turbine subsystemtechnology to a technology readiness status,phase 2[PE-1806-72] B81-14332

Bird flight and airplane flight instruments tomeasure air currents and flight characteristicsCBASA-TB-75777] B81-14962

Bibliography of Supersonic Cruise Research (SCB)program from 1977 to mid-1980[BASA-BP-1063] B81-14973

Experimental determination of unsteady bladeelement aerodynamics in cascades. Volume 2:Translation mode cascade[HASA-CB-165166] B81-14976

AEBOELiSTICIIIPassive control of wing/store flutter

[HASA-TB-81865] B81-13922The effects of warhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] H81-13955

AEBOBAOTICAi EBGIBEEBH6A summary of proposals for airflight research by

the BBPTA81-19298

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 2: User's manual[BASA-CB-3352] H81-13920

Computational aerodynamic design tools andtechniques used at fighter development[HBB-FE-122/S/PUB/13] B81-139SO

Fundamentals of conceptual design optimization ofsubsonic transport aircraft[VTH-LB-292] B81-13951

ABBOHAOIICiL SATELLITESAeronantical-Baritime Engineering satellite /ABES/

program of Japan[IAF PAPEB 80-D-171] A81-18318

A-2

SUBJECT IHDBX AIBCBAPI CiBBIEBS

ABBOSPACB SISTEBSAvionics and displays in a future airspace system

A81-18070AFTERBODIES

An evaluation of wind tunnel test techniques foeaircraft nozzle afterbody testing at transonicBach numbers[AD-A091775] H81-13931

Evaluation of wind tunnel nozzle afterbody testtechniques utilizing a modern twin enginefighter geonetry at Hach numbers from 0.6 to 1.2

IF-17 aircraft[AD-A091545] H81-13932

AB-64 HELICOPTERAdvanced Attack Helicopter /TAH-64/ - Status report

A81-16580AIB BBEATHIH6 EiSISES

A study of air breathing rockets - Subsonic modecombustion[IAF PAPEB 80-F-270] A81-18371

AIB COBBEBTSBird flight and airplane flight instruments to

measure air currents and flight characteristics[HASA-IB-75777] H81-14962

AIB IHTAKBSCurved centerline air intake for a gas turbine

engine[HASA-CASE-LE»-13201-1] H81-14999

AIB JETSExperimental investigations on shock-associated

noiseA81-17735

The Dalembertometer[ISL-CO-220/79] B81-14292

AIB HAVI6ATIOHAutonomous navigation using passively sensed

terrain imagesA81-17977

BNAV benefits today - Today and future requirementsA81-18056

Omega - An economic Loran A replacementA81-18077

Cruise-missile-carrier navigation requirementsA81-18576

Badio navigation for aircraft: HandbookBussian book

A81-18599Hap-type displays for air navigation

A81-19443AIB 10 AIB BBFOELIHG

An investigation of safety hazards and reliabilityproblems in aerial refueling stores[AD-A091788] 1181-13938

AIB TRAFFICTraffic forecasting for the HBIA Hew Biyadh

International AirportA81-18090

AIB TBAFFIC COITBOLThe future ATC system as influenced by advanced

avionicsA81-16586

Airspace analysis in airport system planningA81-18052

Canada's national aviation forecasting modelsA81-18072

Increasing capacity with computer-assisteddecision making airport planning

A81-18080Airport visual approach, guidance and landing

systems - Airline pilots viewpointA81-18083

Bodeling of the terminal area Air TrafficManagement and Control

A81-1808SAirspace simulation in airport system planning

A81-18086The role of aircraft separation assurance in the

cockpitA81-18092

Aeronautical-Baritime Engineering Satellite /ABES/program of Japan[IAF PAPEB 80-D-171] A81-18318

Performance evaluation of an interrogation-replyscheduling technique for a discrete addressbeacon system of radar surveillance andaircraft communication in ATC

A81-19417Southern California aviation system study

[PB80-215544] H81-13916

Bidair and near midair collisions on two- andthree-dimensional curvilinear flight paths[DFVLB-FB-80-13] H81-13944

Hind shear systems integration plan, VICOB (visualconfirmation) reliability analysis[PB80-218233] N81-13919

Proceedings: Fourth Annual Workshop onHeteorological and Environmental Inputs toAviation systems( MASA-CP-2139] H81-14555

Applicated techniques for the control of approachtraffic[DFVLB-BITT-79-20] H81-14992

Advanced flight deck/crew station simulatorfunctional requireaents[HASA-CB-159331] H81-14994

AIB TBASSPOBTATIOBFuel conservation in the air transportation

industry - General and operational aspectsA81-17143

International Air Transportation Conference, BewOrleans, La., April 30-Bay 3, 1979, Proceedings.Volumes 1 5 2

A81-18051Hew major U.S. airports - Capacity considerations

481-18060Aviation assumptions in the eighties

A81-18068A new perspective in aviation systems planning

A81-18069Southern California aviation system study

[PB80-215544] H81-13916AIBBOBHE EQUIPSBBT

Principle for the design of hybrid control systemsfor passenger transport systems

A81-17577Observing lightning from ground-based and airbornestations

H81-14566AIBBOBIE/SPACEBOBIB COSPUTEBS

An overview - 1980 generation avionic developmentsA81-18061

L-1011 Flight aanagement System designconsiderations

A81-18074Computer generated displays and pilot effectiveness

A81-18082System considerations in the implementation ofdigital control[AAS 80-032] A81-19375

AIECHAFT ACCIDEBT IBVESTIGATIOITestimony of Elwood T. Driver, Vice Chairman,national Transportation Safety Board,accompanied by Serrit J. Ralhont, Chief, HumanFactors Division, and Matthew B. BcCormick,Senior Air Safety Investigator, Human FactorsDivision

H81-13934AIBCBAFT ACCIDEHTS

Helicopter alarms - The use of ALAT incident andaccident record cards

A81-16689A survey of propulsion systems'malfunctions/failures resulting in helicoptermishaps

A81-17513Turbulence: From a pilot's viewpoint

H81-14561The microburst: Common factor in recent aircraftaccidents

B81-14571Briefs of accidents involving commuter aircarriers and on-demand air taxi operations, D.S.General Aviation 1978[PB81-101701] H81-14987

AIHCBAFT AHTEHIASVolumetric pattern prediction of antennas onaircraft using the geometrical theory ofdiffraction[DFVIB-FB-80-01] B81-14195

AIBCBAFT BBAKBSToday and the future in aircraft wheel and brake

developmentA81-17046

AIBCBAFT CABBIEBSPlanning for and evaluating the potential of aland based aircraft for carrier operations

A81-19470

A-3

AIBCBAFT COBBOHICATIOH SUBJECT IIDBZ

AIBCBAFT COBBUIICATIOHAutomating airborne company communications

A81-18064Performance evaloation of an interrogation-replyscheduling technique for a discrete addressbeacon systea of radar surveillance andaircraft communication in ATC

A81-19417AIBCBAPT COHPABTHEHTS

Aviation safety: Interior compartment materials[GPO-50-388] H81-13933

AIBCBAFT COIFIGDBAtlOlSFinite difference computation of the steady

transonic potential flov around airplanesA81-17802

Calculation of the lift dependent drag polar ofcambered fighter plane configurations withdeflected maneuver flaps in the subsonic regionby means of a modified procedure according toLamar[DG1B PAPEB 80-109] A81-19395

Drag estimations for stream-line and cylindricalcontour distortions on aircraft fuselages andtrain cars[DGLB PAPEB 80-116] A81-19399

Component-adaptive grid embeddingH81-14697

Experimental aerodynamic characteristics of tvoV/STOL fighter/attack aircraft configurations atBach numbers from 0.4 to 1.4[HASA-TB-81234] H81-14981

Computational Fluid Dynamics, volume 2[VKI-LS-1980-5-VOL-2] 1181-15310

An economic and versatile panel method foraircraft and aircraft/store configurations. Anoutline of the principal features of themathematical modeling and numericalimplementation of the British Aerospace (Harton) 'Bk II Panel Method

H81-15311AI EC BAFT COISTBOCTIOI UIBKULS

Prediction methods for fatigue crack growth inaircraft material

A81-18777Testimony of James J. Kramer, Associate

Administrator for Aeronautics and SpaceTechnology, National Aeronautics and SpaceAdministration, accompanied by John H. Enders,Project Hanager, Aviation Safety TechnologyOffice, John A. Parker, Chemical ResearchProjects Office, NASA-Ames Sesearch Center, andDemitrius A. Kourtides, Chemical BesearchProjects Office, NASA-SUES Besearch Center

H81-13935Testimony of Bichard W. Taylor, Vice President and

Special Assistant to the President, and EugeneA. Bara, Chief Engineer, Payloads Systems,Boeing Commercial Airplane Company

H81-13936Testimony of a panel consisting of: Lloyd E.

Frisbee, Vice President, Engineering andOperations, Lockheed California Company; Lyle A.Iright, Director, Powerplant Engineering,Douglas Aircraft Company, accompanied by DoctorH. C. Schjeldernp, chief Technology Engineer,Baterials and Process Engineering, and F. E.Duskin, Senior Design Engineer, InteriorsEngineering, Douglas Aircraft Company

H81-13937AIBCBAFT COITBOL

Inverse problems of controlled flight dynamics -Longitudinal motion

A81-16968Principle for the design of hybrid control systems

for passenger transport systemsA81-17577

Modeling of the terminal area Air TrafficManagement and Control

A81-18085Bodel-following system with assignable error

dynamics and its application to aircraftA81-18577

System considerations in the implementation ofdigital control[ A A S 80-032] A81-19375

Landing flying qualities evaluation criteria foraugmented aircraft[HASA-CB-163097] H81-13969

Theoretical investigation of the influence ofspoiler dynamics on the handling qualities of anaircraft with direct lift control[DFVLB-FB-80-07] H81-13975

AIBCBAFT DESIGg757/767 design considerations for improved

productivityA81-16584

Development and certification of the Gulfstream IIIA81-16587

A case study in aircraft design: The de Havillandfamily of STOL commuter aircraft Book

A81-16717Concorde aerodynamics and associated systems

development BookA81-16718

The Grnaman Aerospace and Gnlfstream AmericanGulfstream III case study in aircraft designBook

A81-16720The Gossamer Condor and Albatross: A case study in

aircraft design Book[AV-B-80/540] A81-16721

Optimum selection of main parameters for thereverse design of a supersonic military aircraft

A81-17047Transonic axisymmetric bodies with minimal nave drag

A81-17048Application of fracture mechanics in designinglover wing skin of transport aircraft

A81-17049Becent selected papers of NorthwesternPolytechnical University. Parts 162 Book

A81-17801Second order approximation theory of an arbitrary

aerofoil in incompressible potential flovA81-17803

Aerodynamic calculations and design of subcriticalaerofoils

A81-17804Structural analysis .of fuselages with cutouts byfinite element method

A81-17816The matrix analysis of vings

A81-17818Sukhoi's pivotal interdictor

A81-17832Avionics and displays in a future airspace system

A81-18070A summary of proposals for airflight research bythe BBFT

A81-19298Stress measurements on landing gear for the AirbusA-300 B2

AB1-19299Design to cost and new technologies

A81-19347Procedures for optimal drag design of camber and

flap deflection in supersonic regions withconsideration to geometric limits[ D G L B PAPEB 80-110] A81-19396

Circulation Control iing /CCS/ flight tests481-19469

Industry proposes supersonic V/STOLA81-19490

Fighters for the 1990sA81-19497

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 2: User's manual[NASA-CB-3352] B81-13920

Computational aerodynamic design tools andtechniques used at fighter developmentCBBB-FE-122/S/POB/13] H81-13950

Fundamentals of conceptual design optimization ofsubsonic transport aircraft[VTB-LB-292] H81-13951

Laninar-airfoils for transport aircraft[DFVLB-BITT-80-07] H81-13952

Technological forecasting—aircraft design.Citations from the International Aerospace databasetHASA-CB-163833] N81-13957

Economic evaluation of flying-qualities designcriteria for a transport configured with relaxedstatic stability[HASA-TP-1760] H81-13968

Bird flight and airplane flight instruments tomeasure air currents and flight characteristics[HASA-TB-75777] H81-14962

1-4

SUBJECT IIDBI AIRCRAFT HOI SB

A systen for aerodynamic design and analysis ofsupersonic aircraft. Part 1: Generaldescription and theoretical developmentCNASA-CB-3351] H81-14970

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 3: COBputer programdescription[HASA-CB-3353] N81-14971

Remotely piloted vehicles. Citations from theInternational Aerospace abstracts data base[H4S1-CB-163864] B81-14996

&IECBAFT BNGIIESProductivity - The challenge of aircraft and

engine maintenance481-17045

Bolls-Boyce engines status reportA81-17166

Coatings in the aero gas turbineA81-17167

Turbopropeller engine PZL-10SA81-17324

Composition of sludge formed in B-3V oilA81-17373

Joint-laboratory qualification testing of oils forgas turbine engines

A81-17375The digital control system as part of an

integrated accessory fit for fntuce enginesA81-17505

Turbine blade technology - Present and futureIISVS PAPEB 80-C2/ABBO-10] A81-18639

Calculated and experimental data for a 118-nm boreroller bearing to 3 million DH[ASME PAPEB 80-C2/LUB-14] A81-18668

Aircraft engine programs employing cost objectivesA81-19346

Calculation of propeller efficiency for an idealpropeller

A81-19444An evaluation of wind tunnel test techniques for

aircraft nozzle afterbody testing at transonicBach numbers[AD-A091775] H81-13931

Advanced Technology Spark-Ignition Aircraft PistonEngine Design Study[NASA-CB-165162] N81-13963

Prevention of spline wear by soft metallic coatingsaircraft engines

[AD-A091861] N81-14064Compressor configuration and design optimization

for the high reliability gas turbine[DOE/ET-15425/T1] H81-14327

The measurement of aero gas turbine noise[PNB-90032] H81-14795

Analysis of pressure spectra measurements in aducted combustion systemCNASA-TH-81583] H81-15768

AIBCBAFI EQOIPHEITA fault tolerant multiprocessor system with

reconfiguration suitable for mnltiazial flightstabilization and trimming

481-19296Solid-state power systen use expands

A81-19491Evaluation of a computer-generated perspective

tunnel display for flight path following[HASA-TP-1736] N81-13958

Flight evaluation of the terminal guidance system[HASA-CH-163859] H81-14991

AIBCBAFT FDELSFormation of solid phase during the heating of jet

fuelsA81-17372

Testimony of Elwood I. Driver, Vice Chairman,national Transportation Safety Board,accompanied by Gerrit J. Halhout, Chief, HumanFactors Division, and Hatthew H. HcCoriuick,Senior Air Safety Investigator, Human FactorsDivision

881-13934AIBCBAFI GUIDANCE

Airport visual approach, guidance and landingsystems - Airline pilots viewpoint

A81-18083AIBCBAFI HAZARDS

An investigation of safety hazards and reliabilityproblems in aerial refueling stores[AD-A091788] H81-13938

Aeronautical concerns and Rational Aeronautics andSpace Administration atmospheric electricityprojects

N81-14567The microburst: Common factor in recent aircraft

accidentsN81-14571

Doctor Fujita's microbarst analysis at ChicagoN81-14572

Lightning. Citations from the InternationalAerospace abstracts data base[NASA-CR-163857] N81-15614 8

Clean air turbulence. Citations from theInternational Aerospace Abstracts data base[NASA-CB-163863] N81-15649

AIBCBAFI BIDBADLIC SISTERSElimination of vibrations in aircraft piping systems

Bussian bookA81-18497

AIRCRAFT IBDOSTBIAviation assumptions in the eighties

A81-18068An assessment of General Aviation utilization of

advanced avionics technology[NASA-CB-159328] 881-13941

Current aircraft survey (approach speeds, grossweights, and Dimensions)[PB80-225691] H81-13956

AIBCBAFI IISIBDBEITSA new system for the study of visual information

presentation in aeronautics - GIBIA81-16688

Radio navigation for aircraft: HandbookRussian book

A81-18599Simulator study of conventional general aviation

instrument displays in path-following tasks withemphasis on pilot-induced oscillations[HASA-TP-1776] N81-14997

AIBCBAFI LANDINGMicro-wave landing system - An operational point

of viewA81-18055

Flight instrumentation requirements forall-weather approach and landing

A81-18059Experimental investigation of orographic waves and

vertical motions in the Krasnovodsk airport areaA81-19441

Flight evaluation of the terminal guidance systemtHASA-CB-163859] N81-14991

AIBCBAFI MAIITBSAMCBProductivity - The challenge of aircraft and

engine maintenanceA81-17045

Issues regarding Army tnrboshaft enginesdiagnostics and condition monitoring

A81-17514Aircraft maintenance, citations from the

International Aerospace Abstracts data baseCNASA-CB-163837] N81-13917

AIBCBAFI MAMBUTBBSThe effect of aerodynamic coupling on the dynamics

of aircraft in fast rolling motionA81-17471

Drag reduction through formation flight[DGLR PAPEB 80-106] A81-19393

Planning for and evaluating the potential of aland based aircraft for carrier operations

A81-19470Maneuvering aircraft: Noise pollution and

control. Citations from the HTIS data base[PB80-815566] H81-14525

AIRCRAFT MODELSTesting model rotorcraft for overwater operations

A81-18058AIBCBAFI BOISE

The federal role in airport noise control planningA81-18073

The sonic boom from an aircraft flying along anarbitrary path in a stratified atmosphere in thepresence of a three-component wind

A81-19636Maneuvering aircraft: Noise pollution and

control. Citations from the NTIS data base[PB80-815566] N81-14525

Assessment of ground effects on the propagation ofaircraft noise: The T-38A flight experiment[NASA-IP-1747] N81-14788

A-5

AIRCRAFT P1HIS SUBJECT IIDBI

The rating of helicopter noise: Development of aproposed impulse correction[NPL-AC-93] H81-11792

The annoyance caused by noise around airports[HASA-TH-75784] H81-15579

Aircraft annoyance evaluations asing field andlaboratory simulation techniques[DTIAS-248] H81-15580

AIRCBAFT PARISRenewal function for any arbitrary period - A

Bayesian nayA81-16939

The rigidity and performance of a siaple spiralbevel helicopter gearbox[ASHE PAPER 80-C2/DET-103] A81-18654

Performance of computer-optimized tapered-rollerbearings to 2.4 million DN[ASHE PAPER 80-C2/LUB-18] A81-18672

The vear of PTFE-containing dry bearing linerscontaminated by fluids[ASLE PBEPHIHT 80-LC-6B-3] A81-18758

URCBAFT PERFORHARCEF/A-18 full scale development test

A81-16579The Grumman Aerospace and Gulfstrean American

Gulfstream III case study in aircraft designBook

A81-16720The Gossamer Condor and Albatross: A case study inaircraft design Book[AV-B-80/540] A81-16721

History of flight testing the L-1011 Tristar jettransport. I - The L-1011-1

A81-17976AIECBAFT PILOTS

Primary training of military pilots - Changingtheories and new trainers

A81-19498Turbulence: From a pilot's viewpoint

N81-14561AIRCRAFT PEODOCTIOS

The Grumman Aerospace and Gnlfstream AmericanGnlfstream III case study in aircraft designBook

A81-16720Automatization of the adhesion process for

supporting airframe parts in light contour systemsA81-19297

AIRCBAFT PRODOCTIOI COSTSThe design-to-cost of aircraft

A81-19344Design to cost and new technologies

A81-19347»IECBAFT BELIABILITI

A case study on the F-16 fly-by-wire flightcontrol system Book

A81-16719The problems of helicopter ditching

A81-18071AIRCBAFT SAFETY

Sarsat - A rescue system for ships and aircraftA81-16684

Safety considerations for helicopter drive systemsof the 1980s

A81-17510Helicopter survivability in overwater situations

A81-18081Pyrotechnics serving safety in aircraft air

and ground escape systemsA81-19348

Aviation safety: Interior compartment materials[GPO-50-388] H81-13933

Testimony of James J. Kramer, AssociateAdministrator for Aeronautics and SpaceTechnology, National Aeronautics and SpaceAdministration, accompanied by John H. Enders,Project Nanager, Aviation safety TechnologyOffice, John A. Parker, Chemical BesearcbProjects Office, HASA-Ames Research Center, andDeoitrios A. Konrtides, Chemical ResearchProjects Office, NASA-ABES Research Center

H81-13935Testimony of Richard B. Taylor, Vice President and

Special Assistant to the President, and EugeneA. Bara, Chief Engineer, Payloads Systems,Boeing Commercial Airplane Company

N81-13936

Testimony of a panel consisting of: Lloyd E.Frisbee, Vice President, Engineering andOperations, Lockheed California company; Lyle A.(right. Director, Powerplant Engineering,Douglas Aircraft Company, accompanied by DoctorB. c. Schjelderup, Chief Technology Engineer,Materials and Process Engineering, and F. E.Dnskin, senior Design Engineer, InteriorsEngineering, Douglas Aircraft Company

H81-13937Proceedings: Fourth Annual Workshop on

Meteorological and Environmental Inputs toAviation systems[NASA-CP-2139] H81-14555

Aviation meteorology research and development: Astatus report

H81-14557measuring weather for aviation safety in the 1980's

N81-14568Commuter airline safety

[PB81-1 04267] B81-14988AIRCBAFT SPECIFICATIONS

Current aircraft survey (approach speeds, grossweights, and Dimensions)[PB80-225691] H81-13956

AIRCBAFT STRUCTURESThe automatic matrix force method and techniques

for handling more complex computations withgiven computer capacity

A81-17815Elimination of vibrations in aircraft piping systems

Russian bookA81-18497

Automatization of the adhesion process forsupporting airframe parts in light contour systems

A81-19297The effects of warhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] N81-13955

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] H81-14300

AIRCRAFT SORVIVABILITIHelicopter survivability in overwater situations

A81-18081Aviation safety: Interior compartment materials

[GPO-50-388] N81-13933AIRCRAFT TIRES

Today and the future in aircraft wheel and brakedevelopment

A81-17046AIRFIELD SURFACE BOVEBBITS

Non-destructive pavement evaluationA81-18062

AIRFOIL PROFILESVariational principles and generalized variational

principles for the hybrid aerodynamic problem ofairfoil cascades on an arbitrary stream sheet ofrevolution

A81-17741Second order approximation theory of an arbitrary

aerofoil in incompressible potential flowA81-17803

Aerodynamic calculations and design of snbcriticalaerofoils

A81-17804Reduction of profile drag by blowing out through

peg holes in areas of streamline separationbubbles[DGLB PAPER 80-103] A81-19392

Experimental investigation of a right angle wingwith partially separated flow with and withoutground effects[DGLR PAPER 80-111] A81-19397

Wind-tunnel test of an articulated helicopterrotor model with several tip shapes[NASA-TB-80080] H81-13918

AIRFOILSA computer program for the design and analysis of

low-speed airfoils, supplement[HASA-TH-81862] 1181-13921

Surface finishing[BASA-CASE-HSC-12631-3] H81-14077

Experimental determination of unsteady bladeelement aerodynamics in cascades. Volume 2:Translation mode cascade[SASA-CB-165166] N81-14976

A-6

SUBJECT ISDBI APPBOACH COIIB01

A nethod for obtaining shockless transonic flowspast airfoils, partially modified from a givenarbitrary airfoil[NAL-TB-602T] N81-14983

AIBPBA8ESfieview of engine/airframe/drive train dynamic

interface development problems481-17516

Engine-airframe transient compatibility - Analysisand test

481-17517Automatization of the adhesion process for

supporting airfrane parts in light contour systems481-19297

AIBLINE OPEBATIOiSThe future 4TC system as influenced by advanced

avionics481-16586

Airline flight departure procedures - Choosingbetween noise abatement, minimum fuelconsumption and mininum cost

481-17011Productivity - The challenge of aircraft andengine maintenance

481-17015An overview - 1980 generation avionic developments

481-18061Aircraft maintenance. Citations from the

International Aerospace Abstracts data base(SASA-CB-163837J H81-13917

Commuter airline safety[PB81-104267] H81-11988

AIBPOBT LIGHTSAirport visual approach, guidance and landing

systems - Airline pilots viewpoint181-18083

AIBPOBT PLAN BUGAirspace analysis in airport system planning

A81-18052Introduction to a rigid pavement design procedure

A81-18051Micro-wave landing system - An operational point

of viewA81-18055

The introduction of STOL and BNAV to largecommercial operations

A81-18057New major O.S. airports - Capacity considerations

A81-18060Community participation in airport planning

A81-180674 new perspective in aviation systems planning

481-18069Canada's national aviation forecasting models

481-18072The federal role in airport noise control planning

481-18073Fully bonded concrete overlay for an airport runway

481-18075Investment decision-making in international airports

481-18079Increasing capacity with computer-assisted

decision making airport planning481-18080

Design of the new Tehran International Airport481-18081

Modeling of the terminal area 4ir TrafficManagement and Control

481-18085Airspace simulation in airport system planning

481-18086The importance of 'Interim Standard MicrowaveLanding System' for small community airports

481-180874irport/environs plan making - Managing the

planning process481-18088

Bnnway Configuration Management System concepts481-18089

Traffic forecasting for the BBIA Sen BiyadhInternational Airport

481-18090Environmental aspects of airport planning

481-18091Saudi Arabia's new Gateway Airports

A81-18093Southern California aviation system study

[PB80-2 155111 ] H81-13916

4IBPOBTSInternational Air Transportation Conference, HewOrleans, La., April 30-Hay 3, 1979, Proceedings.Volumes 162

481-18051Non-destructive pavement evaluation

481-18062Prestressed concrete airfield pavements

481-18063Bnnway rehabilitation, Washington National Airport

4B1-18066OK pavement design and evaluation - 4 new approach

481-18076Experimental investigation of orographic waves andvertical motions in the Krasnovodsk airport area

481-191111Statistical relationship between median visibility

and conditions of vorstcase manmade impact onvisibility[L4-OE-80-2185] H81-14550

Applicated technigues for the control of approachtraffic[DFVLB-MITT-79-20] N81-11992

The annoyance caused by noise around airports[NASA-TM-75781] N81-15579

Aircraft annoyance evaluations using field andlaboratory simulation techniques[UTI4S-248] N81-15580

4IBSP4CBairspace analysis in airport system planning

481-180524LL-iB4TBBH 41B HATIGATIOB

Problems of flight mechanics involved inall-weather helicopter operation

481-17167Sukhoi's pivotal interdictor

481-17832Helicopters - Help for the all weather terminal

481-18065ALL-iBATBEB LASDIHG SISTERS

Flight instrumentation reguirements forall-weather approach and landing

481-18059ALPHA JET 4IBCB4FT

Planning for and evaluating the potential of aland based aircraft for carrier operations

481-19470ALOMIHOH ALLOTS

Prediction methods for fatigue crack growth inaircraft material

481-18777AMPHIBIOUS fEHICLES

Heave instabilities of amphibious air cushionsuspension systems[OTIAS-216] N81-15156

ANGLE OF ATTACKLaminar boundary layer on swept-back wings ofinfinite span at an angle of attack

A81-17656Characteristics of the velocity field near a

wing-body combination located at an angle ofattack to an oncoming supersonic flow

A81-19337Hypersonic gas flow over a delta wing

A81-19632Aerodynamic side-force alleviator Deans

[NASA-CASE-LAB-12326-1] N81-11968Effects of angle of attack and ventral fin on

transonic flutter characteristics of anarrow-wing configuration[HASA-TM-81911] N81-15397

AIGOLAB ACCELBBATIOICalculated and experiiental.data for a 118-mm bore

roller bearing to 3 million DN[ASHE PAPER 80-C2AOB-14] A81-18668

Performance of computer-optimized tapered-rollerbearings to 2.4 million DN[ A S M E PAPEB 80-C2/LOB-18] A81-18672

AiTIOIIDAITSComposition of sludge formed in B-3f oil

A81-17373APPBOACH COHTBOL

Flight instrumentation regnirements forall-weather approach and landing

A81-18059Airport visual approach, guidance and landing

systems - Airline pilots viewpointA81-18083

1-7

APPBOIIBATIOI SOBJECT IIDBI

The importance of 'Interim Standard BicrowaveLanding System' for small comnnnity airports

A81-18087Flight evaluation of the terminal guidance system

[BASA-CB-163859] B81-14991Applicated techniques for the control of approach

traffic[DPVLB-BITT-79-20] H81-14992

APPBOIIBATIOISecond order approximation theory of an arbitrary

aerofoil in incoopressible potential flowA81-17803

Daal nethods and approxiaation concepts instructural synthesis[HASA-CB-3226] B81-14347

ABE1 IAVIG&TIOBBSAV benefits today - Today and fu ture requirements

A81-18056ABB01 BIHGS

Leading-edge deflection optimization for a highlyswept arrow wing configuration[BASA-TP-1777] B81-14974

Effects of angle of attack and ventral fin ontransonic flutter characteristics of anarrov-wing configuration[BASA-TH-81914J N81-15397

ASTHPTOTIC HETHODSBenewal function for any arbitrary period - A

Bayesian wayA81-16939

ATLABTIC OCEAHCatalog of sea state and wind speed in the South

Atlantic Bight[NASA-CB-156872] 881-14601

AIHOSPBEBIC BLBCTHICITIObserving lightning from ground-based and airborne

stationsB81-14566

Aeronaatical concerns and Bational Aeronautics andSpace Administration atmospheric electricityprojects

B81-14567Lightning. Citations from the International

Aerospace abstracts data base[HASA-CB-163857] B81-15648

ATBOSPHEBIC STBATIFICATIOHThe sonic boom from an aircraft flying along an

arbitrary path in a stratified ataosphere in thepresence of a three-component wind

A81-19636AIHOSPBEBIC TEHPERATOBE

Aircraft icing instrumentation: Unfilled needsrotary wing aircraft

N81-14560ATHOSPHEEIC TDBBDLESCE

Survey of Workshops on Heteorological andEnvironmental Inputs to Aviation Systems

H81-14556Turbulence: From a pilot's viewpoint

N81-14561ATTACK AIBCBAFT

Sukhoi's pivotal interdictorA81-17832

Experimental aerodynamic characteristics of twoV/STOL fighter/attack aircraft configurations atBach numbers from 0.4 to 1.4[NASA-TB-81234] H81-14981

ADTOBATIC COBT1OLPrinciple for the design of hybrid control systems

for passenger transport systemsA81-17577

Gas turbine engines and transmissions for busdemonstration programs[COO-4867-07] N81-14329

AUTOMATIC PLIGHT COHTBOLInverse problems of controlled flight dynamics -

Longitudinal motionA81-16968

Beaotely piloted vehicles, citations from theInternational Aerospace abstracts data base[HASA-CB-163864] B81-14996

AUTOMATIC PILOTSAatononons navigation using passively sensed

terrain imagesA81-17977

AOTOBATIOIAutomating airborne company communications

A81-18064

A?IOHICSAir traffic management enhancement through new

avionics /4-D/A81-16583

A cockpit view of advanced airline avionicsA81-16585

The future ATC system as influenced by advancedavionics

A81-16586An overview - 1980 generation avionic developments

A81-18061Avionics and displays in a future airspace system

A81-18070Cruise-aissile-carrier navigation requirements

AS 1-18576System considerations in the implementation ofdigital control[AAS 80-032] A81-19375

Solid-state power system use expandsA81-19491

Fighters for the 1990sA81-19497

An assessment of General Aviation utilization ofadvanced avionics technology[HASA-CB-159328] B81-13941

DC-to-DC power supply for light aircraft flighttesting[BASA-CB-163850] H81-14989

A survey of new technology for cockpit applicationto 1990's transport aircraft simulators[HASA-CB-159330] H81-14993

Validation Bethods Besearch for Fault-TolerantAvionics and Control Systems Sub-Borking GroupHeeting. CASE 3 peer review[BASA-CP-2167] H81-15702

AXIAL FL01Sound radiation from a finite length unflanged

circular duct with uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712AXIAL FLO! TDBBIBES

The velocity induced by the wake of a wind turbinein a shear layer, including ground effect[FFA-TH-HO-2189-PT-3] H81-14985

AXISIBHBTBIC FLO!Effects of axisymmetric sonic nozzle geometry on

Hach disk characteristicsA81-18022

BBAFFLES

Low-speed wind-tunnel tests of two weathercockingsensors[ISBL-0171-TB] H81-14575

BASE PHBSSOBBAn investigation of support-interference effects

[HAL-TB-622] H81-14984BAI8S THBOBEB

Benewal function for any arbitrary period - ABayesian way

A81-16939BEABIBG ALLOTS

Surface analysis of bearing steels after solventtreatments. II - Lubricant-coated bearing surfaces[ASLE PBEPBIBT 80-LC-8A-6] A81-18748

BEABIBGSExperience with advanced high performance gear steel

for CH-47[ASHE PAPEB 80-C2/DET-77] A81-18648

The wear of PTPE-containing dry bearing linerscontaminated by fluidsC A S L E PBEPBIBT 80-LC-6B-3] A81-18758

Service life determination for the OH-60-A (OTTAS)helicopter elastomeric bearings[AD-A091756] B81-14324

Improved capabilities to detect incipient bearingfailuresCAD-A091687] H81-14325

BIBLIOSBAPHIESAircraft maintenance. Citations from the

International Aerospace Abstracts data base[SASA-CB-163837] B81-13917

Microwave landing systems. Citations from theEngineering Index data base[PB80-814643] B81-13947

A -8

SUBJECT IHDEX CEHAHICS

Bicrovave landing systems. Citations from theBUS data base[PB80-814635] H81-13948

Technological forecasting—aircraft design.Citations from the International Aerospace database[HASA-CB-163833] B81-13957

Maneuvering aircraft: Noise pollution andcontrol. Citations from the BUS data base[PB80-815566] B81-14525

Bibliography of Supersonic Cruise Besearch (SCB)prograa from 1977 to mid-1980[H4SA-HP-1063] B81-14973

Bemotely piloted vehicles. Citations from theInternational Aerospace abstracts data base[BASA-CB-163864] H81-14996

Lightning, citations froa the InternationalAerospace abstracts data base[HASA-CB-163857] H81-15648

Clean air turbulence. Citations from theInternational Aerospace Abstracts data base[HASA-CB-163863] B81-15649

BIBD-AIiCBAFT COLLISIOISCollisions between aircraft and birds

A81-19445BIHOS

Bird flight and airplane flight instruments tomeasure air currents and flight characteristics[HASA-TH-75777] 1181-14962

BLADE TIPSRind-tunnel test of an articulated helicopter

rotor model with several tip shapes[HASA-TH-80080] H81-13918

BLOiBBSNoise and noise abatement in fans and blowers: A

review[DFVLB-FB-80-16] B81-14796

BLOIIB6Reduction of profile drag by blowing out through

peg holes in areas of streamline separationbubbles[DGLB PAPEB 80-103] A81-19392

BODI-BTBG CONFIGOBATIONSCharacteristics of the velocity field near a

wing-body combination located at an angle ofattack to an oncoming supersonic flow

A81-19337Development of finite-volume methods for

three-dimensional transonic flows[AD-A090829] B81-14986

BOBIie AIBCBAFTTestimony of Bichard I. Taylor, Vice President and

Special Assistant to the President, and EugeneA. Bara, chief Engineer, Payloads Systems,Boeing Commercial Airplane Company

B81-13936BOEING 757 AIBCBAFT

757/767 design considerations for improvedproductivity

A81-16584Computer generated displays and pilot effectiveness

A81-18082BOEIHG 767 AIBCBAFT

757/767 design considerations for improvedproductivity

A81-16584Computer generated displays and pilot effectiveness

A81-18082BOOSTEBS

The T700 booster engineA81-17506

BOOBDABI LAIKB COBTBOLA computer program for the design and analysis of

low-speed airfoils, supplement[NASA-Tn-81862] B81-13921

Active flutter suppression on an F-4F aircraftwith external stores using already existingcontrol surfaces[HBB-FE-17/S/POB/24] 881^13972

Aerodynamic side-force alleviator means[ BASA-CASE-LAB-12326-1 ] H81-14968

BODHDABI LAIEB FLO!Hind-tunnel measurements and comparison with

flight of the boundary layer and heat transferon a hollow cylinder at Bach 3[NASA-TP-1789] B81-14975

BOONDABI LAIEB TBABSITIOBThren-dimensional boundary layer transition via

the mechanisms of 'attachment linecontamination1 and 'cross flow instability1

A81-18122Ball cooling and the laminar-turbulent boundary

layer transition at supersonic flow velocitiesA81-19644

BOOIDABT TILDE PBOBLEHSComponent-adaptive grid embedding

B81-11697An analytic model of subsonic flow around anairflow with a spoiler

B81-14966A method for obtaining shockless transonic flows

past airfoils, partially modified from a givenarbitrary airfoil[BAL-TR-602T] B81-14983

BBOADCASTHGCanada's national aviation forecasting models

A81-18072

CALIFORNIASouthern California aviation system study

CPB80-215544] N81-13916CABABD CONFIGOBATIONS

Computational aerodynaaic design tools andtechniques used at fighter development[UBB-FE-122/S/POB/13] N81-13950

CANOPIESA contribution to stabilization of flight vehicle

parachute systems[DFVLB-HITT-80-05] N81-13926

CABBON FIBEB BEIBFOBCBD PLASTICSConstant-amplitude and flight-by-flight tests on

CEBP specimens[HBB-FE-2/S/POB-26] B81-14006

CABBON FIBBBSA resin injection technique for the fabrication of

aero engine composite components[PBB-9002U] H81-14004

CABTESIAN COOBDIBATESComponent-adaptive grid embedding

B81-14697CASCADE FLOW

Variational principles and generalized variationalprinciples for the hybrid aerodynamic problem ofairfoil cascades on an arbitrary stream sheet ofrevolution

A81-17741An aerodynamic design method for transonic axialflow compressor stage

A81-17805Experimental determination of unsteady blade

element aerodynamics in cascades. Volume 2:Translation mode cascade[NASA-CB-165166] B81-14976

Supersonic stall flutter of high speed fans inturbofan engines[HASA-TH-81613] N81-14978

Solution of plane cascade flow using improvedsurface singularity methods application ofpanel method to internal aerodynamics[HASA-Tn-81589] H81-14979

Full potential solution of transonic quasi-3-Dflow through a cascade using artificialcompressability[NASA-TB-81637] B81-14980

CASE HISTOBIBSA case study on the F-16 fly-by-wire flight

control system BookA81-16719

CATESOBIBSCurrent aircraft survey (approach speeds, gross

weights, and Dimensions)[PB80-225691] B81-13956

CA7ITATIOH FLOBBeduction of profile drag by blowing out through

peg holes in areas of streamline separationbubbles[DGLB PAPEB 80-103] A81-19392

CEBABIC HOSEICOHBSImproved ceramic heat exchanger materials

[BASA-CB-159678] B81-14082CEBAHICS

Improved ceramic heat exchanger materials[NASA-CB-159678] N81-14082

A-9

CBBTIFICATIOB SUBJECT ISDEI

CBBTIFICATI01History of flight testing the 1-1011 Tristar jet

transport. I - The L-1011-1A81-17976

CH-47 HBLICOPTBBExperience with advanced high performance gear steel

for CH-47[ASSE PAPEB 80-C2/DET-77] A81-18648

CBAHBE1 FLOiPropagation of three-dimensional acoastic

perturbations in channels of variablecross-sectional area at frequencies close tocutoff frequency

A81-19338CHABBBLS (DATA TRABSBISSIOB)

A survey of new technology for cockpit applicationto 1990*s transport aircraft simulators[BASA-CB-159330] B81-14993

CHEBICAL COBPOSITIOiComposition of sludge formed in B-3V oil

A81-17373CBBOBIOB STEELS

The effect of cyclic loading on the apparentcleavage fracture toughness of 1Cr-Ho-V rotorsteel

A81-17488CIBCDIT PHOTECTIOI

A case study on the F-16 fly-by-wire flightcontrol system Book

A81-16719Lightning. Citations from the International

Aerospace abstracts data base[HASA-CB-163857] H81-15648

CIRCULATION COHTBOL AIBFOILSCirculation Control Bing /CCw/ flight tests

A81-19469CIVIL AVIATIOS

A cockpit view of advanced airline avionicsA81-16585

The future ATC system as influenced by advancedavionics

A81-16586Design of the new Tehran International Airport

A81-18084Saudi Arabia's new Gateway Airports

A81-18093Pyrotechnics serving safety in aircraft air

and ground escape systemsA81-19348

Aircraft maintenance. Citations from theInternational Aerospace Abstracts data base[NASA-CB-163837] M81-13917

An assessment of General Aviation utilization ofadvanced avionics technology[BASA-CB-159328] B81-13941

The future of civil turbo-fan engines[PBB-90034] 1181-13964

Briefs of accidents involving commuter aircarriers and on-demand air taxi operations, O.S.General Aviation 1978[PB81-101701] H81-14987

Commuter airline safety[PB81-104267] H81-14988

CLBABIHGSurface analysis of bearing steels after solvent

treatments. II - Lubricant-coated bearing surfaces[ASLE PBEPBIHT 80-LC-8A-6] A81-18748

CLKAB AIB TOBBOLEICEClear air turbulence: Historical comments

B81-14562Clean air turbulence. Citations froa the

International Aerospace Abstracts data base[BASA-CB-163863] H81-15649

CLEAVAGE

The effect of cyclic loading on the apparentcleavage fracture toughness of 1Cr-Ho-V rotorsteel

A81-17488COCKPIT SIHOLATOBS

A survey of new technology for cockpit applicationto 1990's transport aircraft simulators[BASA-CB-159330] B81-14993

COCEPITS757/767 design considerations for improved

productivityA81-16584

A cockpit view of advanced airline avionicsA81-16585

The role of aircraft separation assurance in thecockpit

A81-18092COHBBBBT ACOOSTIC BADIATIOB

Improved methods for fan sound field determination[BASA-CB-165188] B81-15769

COLLISION AVOIDABCBThe role of aircraft separation assurance in the

cockpit181-18092

Satellites to aid flight safety[IAF PAPEB 80-IAA-17] A81-18410

Collisions between aircraft and birdsA81-19445

Midair and near midair collisions on two- andthree-dimensional curvilinear flight paths[DFVLB-FB-80-13] B81-13944

COBBOSTIOB CHAHBEBSA simple combnstor system for a small gas turbineengine

A81-17503A vaporizing combustor with double combustion spaces

A81-17827An experimental study on kerosene-hydrogen hybridcombustion in a gas turbine combustor

A81-17841Vector and scalar characteristics of opposing jetsdischarging normally into a cross-stream

A81-17997Analysis of pressure spectra measurements in a

ducted combustion system[BASA-TB-81583] B81-15768

COBBOSTIOI EFFICIEBCIA simple combustor system for a small gas turbine

engineA81-17503

COBSABD ABD COBTBOLThe collision course: Conditions, guidance laws

and properties[DFVLB-FB-80-06J B81-13942

COBBEBCIAL AIBCBAFTToday and the future in aircraft wheel and brake

developmentA81-17046

The introduction of STOL and BHAV to largecommercial operations

A81-18057SNIAS helicopters

A81-19342Briefs of accidents involving commuter aircarriers and on-demand air taxi operations, D.s.General Aviation 1978[PB81-101701] N81-14987

Conmuter airline safety[PB81-104267] B81-14988

COBBDBICATIOI BQUIPSEITAutomating airborne company communications

A81-18064COBHOIICATIOB SATELLITES

Aeronautical-Maritime Engineering Satellite /ABES/program of Japan[IAF PAPEB 80-D-171] A81-18318

Satellites to aid flight safety[IAF PiPEB 80-IAA-17] A81-18410

COBPLEI SISTEHSThe method of saperelements in the dynamics ofcomplex structures

A81-16969COHPOSITB BATEBIALS

A resin injection technique for the fabrication ofaero engine composite components[PBB-90024] B81-14004

Constant-amplitude and flight-by-flight tests onCEBP specimens[BBB-FE-2/S/POB-26] H81-14006

Cost/benefit analysis of advanced materialstechnologies for future aircraft turbine engines[BASA-CB-165225] B81-15006

COBPOSITE STBOCTDBESHingeless tailrotor in fiber compositeconstruction and vibration-isolation systems/ABIS, ASIS/ for helicopters[HBB-0D-311-80-0] A81-19300

COBPBESSIBILITISolution of plane cascade flow using improvedsurface singularity methods application ofpanel method to internal aerodynamics[BASA-TB-81589] B81-14979

A-10

SUBJECT IBDEI COHGBBSSIOHAl BEPOHIS

COHPBBSSIBLB BOONDABY LAYBBLaminae boundary layer on svept-back wings of

infinite span at an angle of attackA81-17656

COHPBBSSIBLB FLORInlet flow distortion in tnrbouachinery

[ASHE P4PEB 80-GT-20J A81-17952Influence of free-streaa turbalence intensity on

heat transfer in the two-dimensional turbulentboundary layer of an accelerated compressible flow

A81-17994COHPBBSSOB BLADBS

Becent selected papers of NorthwesternPolytechnical Dniversity. Parts 162 Book

A81-17801An aerodynamic design method for transonic axialflow compressor stage

A81-17805Structure and decay characteristics of turbulence

in the near- and far-wake of a moderately loadedcompressor rotor-blade[ASHE PAPEB 80-GT-95] A81-17951I

COHPBBSSOB EFFICIENCYThe T700 booster engine

A81-17506COHPBBSSOB BOIOBS

Comparison of experimental and computational shockstructure in a transonic compressor rotor[ASHE PAPEB 80-GT-81] A81-17953

COHPBBSSOBSEffects of downstream distance on turbulence decay

for the compressor research facility lowconditioning system[AD-A091543] N81-14276

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15425/T1] N81-14327

COBPOTATIOSiL FLUID DIBASICSThe method of superelements in the dynamics of

complex structuresA81-16969

Computational Fluid Dynamics, volume 2[VKI-LS-1980-5-VOL-2] N81-15310

An economic and versatile panel method foraircraft and aircraft/store configurations. Anoutline of the principal features of themathematical modeling and numericalimplementation of the British Aerospace (Rarton)Hk II Panel Hethod

H81-15311Vortex methods for two- and three-dimensional flov

simulationsH81-15313

COHPOTEB PB06BAHSThe matrix analysis of wings

A81-17818A computer program for the design and analysis of

low-speed airfoils, supplement[NASA-TH-81862] H81-13921

Development of a computer program data base of anavigation aid environment for siaulated IFBflight and landing studies(NASA-TH-80064] S81-13959

Prediction of sound radiated from differentpractical jet engine inlets[NASA-CB-163824] H81-14789

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 3: Computer programdescription[NASA-CB-3353] H81-14971

COHPOtBB SISTERS DESIGIL-1011 Flight Management System design

considerationsA81-18074

COHPOIEB TECHNIQUESA computer-based laser Doppler velocimeter

[DFVLB-HITT-79-14] H81-14289COBPOIBBIZED DESI61

Aerodynamic design of a ducted propeller -Optimization of efficiency

A81-17146Becent selected papers of Northwestern

Polytechnical Dniversity. Parts 162 BookA81-17801

Finite difference computation of the steadytransonic potential flow around airplanes

A81-17802

Aerodynamic calculations and design of subcriticalaerofoils

A81-17804An aerodynamic design method for transonic axial

flow compressor stageA81-17805

An optimum design procedure of total-temperaturethermocouple probes

A81-17807The automatic matrix force nethod and techniques

for handling aore complex computations withgiven computer capacity

A81-17815Structural analysis of fuselages with cutouts byfinite element method

A81-17816The measurement and analysis of station parameters

of a turbojet engineA81-17825

Increasing capacity with computer-assisteddecision making airport planning

A81-18080Airspace simulation in airport system planning

AS 1-18086Frequency-shaped cost functionals - Extension of

linear-quadratic-Gaussian design methodsA81-18578

Performance of computer-optimized tapered-rollerbearings to 2.4 million DN[ASHE PAPEB 80-C2/LDB-18] A81-18672

Application of the HHA design method to anonlinear turbofan engine multivariableNyquist array method[ NASA-CB-163855] H81-15001

COHPOTBBIZBD SIHOLATIOIAirspace simulation in airport system planning

A81-18086The rigidity and performance of a simple spiral

bevel helicopter gearbox[ASHE PAPEB 80-C2/DET-103] A81-18654

An analytic model of subsonic flow around anairflow with a spoiler

N81-14966Advanced flight deck/crew station simulator

functional requirements[NASA-CB-159331] N81-14994

Aerodynamic stability analysis of N A S AJ85-13/planar pressure pulse generatorinstallation[NASA-CB-165141] N81-15004

Computer Generated Imagery (CGI) currenttechnology and cost geasures feasibility study[AD-A091636] N81-15729

COICOBDE AIBCBAFTConcorde aerodynamics and associated systems

development BookA81-16718

CONCBEIESFully bonded concrete overlay for an airport runway

A81-18075Sealing joints and cracks, thin resurfacing, andlocating voids under concrete slabs[PB80-215635] N81-14182

COIFEBEICBSSpecialists' Heeting on Belicopter PropulsionSystems, Rilliamsbnrg, Va., November 6-8, 1979,Technical Papers

A81-17501International Air Transportation Conference, New

Orleans, La., April 30-Hay 3, 1979, Proceedings.Volumes 1 6 2

A81-18051Aviation safety:' Interior compartment materials

[GPO-50-388] N81-13933Proceedings: Fourth Annual Workshop on

Heteorological and Environmental Inputs toAviation systems[NASA-CP-2139] N81-14555

Computational Fluid Dynamics, volume 2[VKI-LS-1980-5-VOL-2] N81-15310

CONFIGOBATIOH HAHAGBHEiTBunway Configuration Hanagement system concepts

A81-18089COI6BESSIOSAL HEPOBTS

Aviation safety: Interior compartment materials[GPO-50-388] N81-13933

A-11

COHICAL NOZZLES SDBJECI IIDBI

TestiBony of Elwood I. Driver, Vice Chairnan,Hational Transportation Safety Board,accompanied by Gerrit J. Halhout, Chief, HumanFactors Division, and Matthew H. McCormick,Senior Air Safety Investigator, Hasan FactorsDivision

N81-13931Testiiaony of James J. Kramer, Associate

Administrator for Aeronautics and SpaceTechnology, Hational Aeronautics and SpaceAdministration, accompanied by John H. Enders,Project Manager, Aviation Safety TechnologyOffice, John A. Parker, Chemical ResearchProjects Office, NASA-Ames Research Center, andDemitrius A. Konrtides, Chemical ResearchProjects Office, NASA-ARES Research Center

N81-13935Testimony of Richard B. Taylor, vice President and

Special Assistant to the President, and EugeneA. Bara, Chief Engineer, Payloads Systems,Boeing commercial Airplane Company

N81-13936Testimony of a panel consisting of: Lloyd E.

Frisbee, Vice President, Engineering andOperations, Lockheed California Company; Lyle A.Hright, Director, Powerplant Engineering,Douglas Aircraft Company, accompanied by DoctorH. c. Schjelderup, Chief Technology Engineer,Materials and Process Engineering, and P. E.Duskin, senior Design Engineer, InteriorsEngineering, Douglas Aircraft Company

N81-13937COHICAL HOZSLES

Static source locations for four nozzles mountedon a J-85 engine[HASA-CR-152101] N81-11998

COHSTBAINTSFundamentals of conceptual design optimization of

subsonic transport aircraft[VTH-Lfi-292] , H81-13951

Economic evaluation of flying-gualities designcriteria for a transport configured with relaxedstatic stability[NASA-TP-1760] H81-13968

CO8STBOCTIOSPrestressed concrete airfield pavements

A81-18063COHSTBUCTIOH HATEBIALS

Introduction to a rigid pavement design procedureA81-1805U

COHTAHIHAITSThe wear of PTFE-containing dry bearing liners

contaminated by fluids[ASLE PREPBIHT 80-LC-6B-3] A81-18758

COHTBOL BOAKDSA survey of new technology for cockpit application

to 1990"s transport aircraft simulators[NASA-CB-159330] H81-11993

COHTBOL SIMULATIONModeling of the terminal area Air Traffic

Management and ControlA81-18085

Airspace simulation in airport system planningA81-18086

COHTBOL STABILITYModel-following system with assignable error

dynamics and its application to aircraftA81-18577

COHTBOL SURFACESAnalysis of unsteady pressure measurements on an

aerofoil section with an harmonicallyoscillating, slotted flap[DFVLB-FB-80-22] N81-13929

System identification of the longitudinal motionof the DFVLB HFB 320 research aircraft withparticular consideration of control surfaceeffectiveness[DFVLH-MITT-79-16] N81-13971

Active flutter suppression on an F-1F aircraftwith external stores using already existingcontrol surfaces[MBB-FE-17/S/POB/2II] H81-13972

Aerodynamic side-force alleviator means[NASA-CASE-LAR-12326-1 ] H81-1U968

COH7ECTIOH COBREHTSBird flight and airplane flight instruments to

measure air currents and flight characteristics[HASA-TM-75777] N81-14962

COBfBBGBHT-DIVBRGEHT HOZZLESInvestigation of convergent-divergent nozzles

applicable to reduced-power supersonic cruiseaircraft[HASA-TP-1766] H81-1I1972

CONVEYORSSystem for refurbishing and processing parachutes

[ NASA-CASE-KSC-11012-1] B81-14967COOLIBG SYSTEMS

Turbine blade technology - Present and future[ ASME PAPER 80-C2/AERO-10] A81-18639

COOEDI BATESGrid generation for general three-dimensional

configurationsB81-11711

CORHOSIOH PREVENTIONThe resistance of tank protective measures to

microorganisms[SHIAS-801-551-107] H81-15072

CORROSION BBSISTAMCBDevelopment of high-temperature turbine subsystem

technology to a technology readiness status,phase 2[FE-1806-72] N81-14332

COST AHALYSISThe design-to-cost of aircraft

A81-19314Aircraft engine programs employing cost objectives

A81-193U6Design to cost and new technologies

A81-193U7Microwave landing systems. Citations from the

Engineering Index data base .[PB80-8116113] H81-13917

Microwave landing systems. Citations from theBTIS data base[PB80-811635] N81-13918

Technological forecasting—aircraft design.Citations from the International Aerospace database[NASA-CB-163833] S81-13957

Cost/benefit analysis of advanced materialstechnologies for future aircraft turbine engines[NASA-CB-165225] B81-15006

Computer Generated Imagery (CGI) currenttechnology and cost measures feasibility study[AD-A091636J N81-15729

COST EFFECTIVENESSAviation assumptions in the eighties

A81-18068Onega - An economic Loran A replacement

A81-18077COST BEDDCTIOI

Productivity - The challenge of aircraft andengine maintenance

A81-17015.A-jcraf t engine programs employing cost objectives

A81-19346Design to cost and new technologies

A81-19317COUPLED BODES

The effect of aerodynamic coupling on the dynamicsof aircraft in fast rolling motion

A81-17II71CRACK PROPAGATION

The effect of cyclic loading on the apparentcleavage fracture toughness of ICc-Mo-V rotorsteel

A81-17488Prediction methods for fatigue crack growth in

aircraft materialA81-18777

CRACKSSealing joints and cracks, thin resurfacing, and

locating voids under concrete slabs[PB80-215635] N81-1U182

CREEP PROPERTIESMechanisms of damage accumulation in

time-dependent cyclic deformation[DOE/EB-10570/1] N81-11363

CRITERIALanding flying qualities evaluation criteria for

augmented aircraft[NASA-CR-163097] B81-13969

CROSS FLO!Vector and scalar characteristics of opposing jets

discharging normally into a cross-streamA81-17997

A-12

SDBJBCT IHDBI DISPLAY DETICBS

Three-dimensional boundary layer transition viathe nechanisas of 'attachment linecontamination' and 'cross floe instability*

181-18122Time dependent Havier-Stokes solution of a

turbulent gas jet ejected fcoa a rectangularorifice into a high-subsonic crossflow

881-14964Aerodynamic side-force alleviator means

[HASA-CASB-LAB-12326-1 ] H81-14968CBOTSB HISSILES

Cruise-missile-carrier navigation requirements481-18576

CBISTAL DISLOCATIONSMechanisms of damage accumulation in

time-dependent cyclic deformation[DOB/EB-10570/1] H81-14363

CYCLIC LOADSThe effect of cyclic loading on the apparent

cleavage fracture toughness of ICr-Ho-V rotorsteel

A81-17488The stress behavior of three advanced nickel base

snperalloys daring high temperature low cyclefatigue[AD-A091694] H81-14061

Mechanisms of damage accuDulation intime-dependent cyclic deformation[DOE/EB-10570/1] B81-14363

Rotor model for verification of coaputation methods[ISD-262] H81-15467

CILIHDBICAL BODIESAerodynamic side-force alleviator means

[NASA-CASE-LAB-12326-1] N81-14968CILIIDBICAL SHELLS

Rind-tunnel measurements and comparison withflight of the boundary layer and heat transferon a hollo" cylinder at Bach 3[HASA-TP-1789] B81-14975

DAHA6BMechanisms of danage accumulation in

time-dependent cyclic deformation[DOE/EB-10570/1] H81-14363

DABPIIG TESTSNondestructive dynamic testing

A81-19657DATA ACQDISITIOB

Botor model for verification of computation methods[ISD-262] H81-15467

DATA PBOCBSSIHGDetection of moving objects Eussian book

A81-18773Statistical relationship between median visibility

and conditions of vorstcase manmade impact onvisibility[LA-BB-80-2485] H81-14550

DATA BECOBDIIGEquipment for testing and measuring a "helmet

mounted sight and display" system with a coupledmovable television camera in theflight-simulator for research of the DFVLB[DFVLB-HITT-80-04] B81-13960

DATA BEDOCTIOIA computer-based laser Doppler velocimeter

[DFVLB-HITT-79-14] H81-14289DATA TBABSHISSIOB

A survey of new technology for cockpit applicationto 1990 *s transport aircraft simulators[HASA-CB-159330] H81-14993

DC 3 AIBCBAFTDC-to-DC power supply for light aircraft flight

testing[HASA-CB-163850] H81-14989

DB 8ATCLLAID AIBCB&FTA case study in aircraft design: The de Bavilland

family of STOL commuter aircraft BookA81-16717

DBCISIOB BAKIHGInvestment decision-making in international airports

A81-18079Increasing capacity with computer-assisted

decision making airport planning481-18080

Airport/environs plan making - Hanaging theplanning process

481-18088

DEFLECTIOBLeading-edge deflection optimization for a highly

swept arrow wing configuration[BASA-TP-1777] B81-14974

DELTA III6SProcedures for optimal drag design of camber and

flap deflection in supersonic regions withconsideration to geometric limits[DGLB PAPEB 80-110] A81-19396

The coordinate-deformation method in the problemof a supersonic gas flow over an airfoildelta Kings

A81-19631Bypersonic gas flow over a delta wing

A81-19632Experimental study of supersonic viscous leeside

flow over a slender delta ving[HASA-TH-81248J H81-14265

DBSCEBT TBAJECTOBIBSAir traffic management enhancement through new

avionics /4-D/A81-16583

DESIGI AIALISISOptimum selection of main parameters for the

reverse design of a supersonic military aircraftA81-17047

OK pavement design and evaluation - A new approachA81-18076

Fundamentals of conceptual design optimization ofsubsonic transport aircraft[VTH-LB-292] . B81-13951

Economic evaluation of flying-qualities designcriteria for a transport configured with relaxedstatic stability[BASA-TP-1760] N81-13968

Full potential solution of transonic guasi-3-Dflow through a cascade using artificialcompressability[NASA-TH-81637] R81-14980

The resonance frequencies of ventilated wind tunnels[ABC-B/B-3841] H81-15009

DETBCTIOIObserving lightning from ground-based and airborne

stationsB81-14566

DIFFBACTIOI PATTBBISVolumetric pattern prediction of antennas on

aircraft using the geoaetrical theory ofdiffraction[DFVLB-FB-80-01] B81-14195

DIFFDSBBSCompressor configuration and design optimization

for the high reliability gas turbine[DOE/ET-15425/T1] H81-14327

DIGITAL SISTEHSA new system for the study of visual information

presentation in aeronautics - GIBIA81-16688

The digital control system as part of anintegrated accessory fit for future engines

A81-17505System considerations in the implementation of

digital control[AAS 80-032] A81-19375

DIBEC1 LIFT COHTBOLSTheoretical investigation of the influence of

spoiler dynamics on the handling qualities of anaircraft with direct lift control[DFVLB-FB-80-07] H81-13975

DIBECTIOHAL COMTBOLThe collision course: conditions, guidance lawsand properties[DFVLB-FB-80-06] H81-13942

DISCBBIE ADDBBSS BBACOI SISCEHPerformance evaluation of an interrogation-reply

scheduling technique for a discrete addressbeacon system of radar surveillance andaircraft communication in ATC

A81-19417DISPLAI DEVICES

4 new system for the study of visual informationpresentation in aeronautics - GIBI

481-16688An overview - 1980 generation avionic developments

A81-18061Automating airborne company communications

A81-18064Avionics and displays in a future airspace system

A81-18070

A-13

DITCHISG (LABDIBG) SDBJECT IIDEI

Computer generated displays and pilot effectivenessA81-18082

The role of aircraft separation assurance in thecockpit

A81-18092Bap-type displays for air navigation

A81-191M3The flying hologram - Latest in head-op displaysystems

A81-19500Evaluation of a computer-generated perspective

tunnel display for flight path following[HiSA-TP-1736] , H81-13958

A survey of new technology for cockpit applicationto 1990's transport aircraft simulators[NASA-CB-159330] B81-1Q993

DITCBIRG (IAIDI1G)Testing model rotorcraft for overwater operations

A81-18058The problems of helicopter ditching

A81-18071Helicopter survivability in overwater situations

A81-18081DOBHBASH

Dowuuash calculation at close range behind atrapezoidal wing in supersonic flow[PFA-TN-AO-1661] 1181-13925

DBAS CHOTESA contribution to stabilization of flight vehicle

parachute systens[DFVLB-HITT-80-05] H81-13926

DBAG BKASOBEBEBTDrag estimations for stream-line and cylindrical

contour distortions on aircraft fuselages andtrain cars[DGLB PAPEB 80-116] A81- 19399

Rind-tunnel measurements and comparison withflight of the boundary layer and heat transferon a hollow cylinder at Bach 3[8ASA-TP-1789] H81-11975

DBAG BBDOCTIOITransonic axisymmetric bodies with minimal wave drag

A81-17018Reduction of profile drag by blowing out through

peg holes in areas of streamline separationbubbles[DGLB PAPEB 80-103] A81-19392

Drag reduction through formation flight[DGLB PAPEB 80-106] A81-19393

Procedures for optimal drag design of canber andflap deflection in supersonic regions.withconsideration to geometric limits[DGLB PAPEB 80-110] A81-19396

Laminar-airfoils for transport aircraft[DFVLB-BITT-80-07] N81-13952

DBOHE &IBCBAFTAerial surveying of small areas from a small

remotely controlled droneA81-17525

DBOPS (LIQUIDS)Fuel injector characterization studies

[8ASA-CB-165200] S81-15003DOCIED FLOI

Analysis of pressure spectra measurements in aducted combustion system[SASA-TB-81583] N81-15768

DIBASIC CHABACTBSISTICSDynamic characteristics of a high-speed rotor with

radial and axial foil-bearing supports[ASBE PAPEB 80-C2/LOB-35] A81-18683

Detection of moving objects Bussian bookA81-18773

A contribution to stabilization of flight vehicleparachute systems[DFVLB-BITT-80-05] B81-13926

DIH1BIC SODELSInverse problems of controlled flight dynamics -

Longitudinal motionA81-16968

Model-following system with assignable errordynamics and its application to aircraft

AB1-18577DIH1BTC PBESSUBE

Advanced ejection seat for high dynamic pressureescape. Bind tunnel test[AD-A091810] M81-13940

DIIABIC BBSPOHSBPeriodically stiffened fluid-loaded plates. I -

Besponse to convectei harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067The effects of warhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A09167U] B81-13955

Experimental analysis and methods to determine thedynamic behavior of propulsion shafting systems

B81-15401Botor model for verification of computation methods

[ISD-262] H81-15167DIBASIC STABILITY.

Beview of engine/airframe/drive train dynamicinterface development problems

A81-17516Engine-airframe transient compatibility - Analysis

and testA81-17517

Heave instabilities of amphibious air cushionsuspension systems[OTIAS-2U6] B81-15156

DI1AHIC.STBDCIOBAL ABALISISPeriodically stiffened fluid-loaded plates. I -

Besponse to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067On the steady state and dynamic performance

characteristics of floating ring bearings[ASBE PAPEB 80-C2/LUB-17] A81-18671

DIIABIC TESTSNondestructive dynamic testing

A81-19657

ECOSOBIC ABALISISTraffic forecasting for the HBIA New BiyadhInternational Airport

481-18090Economic evaluation of flying-gnalities design

criteria for a transport configured with relaxedstatic stability[NASA-TP-1760] N81-13968

ECOSOBIC IBPACTAviation assumptions in the eighties

A81-18068EFFECTITE PBBCBIVED BOISE LEVELS

The rating of helicopter noise: Development of aproposed impulse correction[BPL-AC-93] H81-1U792

EJECTIOB SEATSAdvanced ejection seat for high dynamic pressure

escape. Bind tunnel test[AD-A091810] 881-13940

ELASTOBIDBODIBABICSLubrication of rolling element bearings

A81-18738ELASIOSETEBS

Service life determination for the OH-60-A (DTTAS)helicopter elastomeric bearings[AD-A091756] B81-1«324

ELECTBIC POTBBTIALDC-to-DC power supply for light aircraft flight

testing[BASA-CB-163850] B81-14989

ELECTBIC POBEB SOPPLIESSolid-state power system use expands

A81-19191ELECTBO-OPTICS

Application of optical methods to the study of jetnoise and turbulence[ISL-CO-201/80] B81-15819

ELECTBOHECHABICAL DEVICESA case study on the F-16 fly-by-wire flight

control system BookA81-16719

BLECTBOBIC PACKAGIBGDC-to-DC power supply for light aircraft flight

testing[BASA-CB-163850] B81-14989

ELECIBOPLATIBGPrevention of spline wear by soft metallic coatings

aircraft engines[AD-A091861] H81-1U06U

A-11

SUBJECT IBDBI BXH10ST G1SBS

EHBB6T COISBBVATIOBAirline flight departure procedures - Choosing

between noise abatement, minimum fuelconsumption and minimum cost

A81-17044Fuel conservation in the air transportation

industry - General and operational aspects481-17143

EH6IBE COHTBOLDigital control for helicopter powerplants

181-17504The digital control system as part of an

integrated accessory fit for future enginesA81-17505

Failure Indication and Corrective Action forturboshaft engines

A81-17515Power control for hot gas engines

[NASA-CASE-HPO-14220-1] N81-14318EH6IHB DESIGM

Bolls-Eoyce engines status reportA81-17166

Turbopropeller engine PZL-10SA81-17324

Specialists' Heeting on Helicopter PropulsionSystems, Hilliamsburg, Va., November 6-8, 1979,Technical Papers

A81-17501The impact of contingency ratings on advanced

turboshaft engine designA81-17502

The T700 booster engineA81-17506

Drive system development for the 1980'shelicopter transmissions

A81-17508Development of helicopter transmission componentsfor the 1980s

A81-17509Helicopter propulsion system development and

qualificationA81-17511

Is the engine helicopter-worthyA81-17518

The measurement and analysis of station parametersof a turbojet engine

A81-17825Calculation of propeller efficiency for an ideal

propellerA81-19444

Advanced Technology Spark-Ignition Aircraft PistonEngine Design Study[HASA'CB-165162] N81-13963

Application of the HBA design method to anonlinear tnrbofan engine multivariableNyguist array method[HASA-CB-163855] H81-15001

El SI HE PAIJ.OBEA survey of propulsion systems'

malfunctions/failures resulting in helicoptermishaps

A81-17513Failure Indication and Corrective Action fortnrboshaft engines

A81-17515EIGIBB IILBTS

Exhaust gas reingestion measurements inhelicopters

A81-17521A preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

A81-17824Prediction of sound radiated from different

practical jet engine inlets[BASA-CB-163824] H81-14789

EHSISB BOIITOBIIS IISTBOHBBISFailure Indication and Corrective Action for

turboshaft enginesA81-17515

BBSIHE IOISEPropagation of three-dimensional acoustic

perturbations in channels of variablecross'Sectional area at frequencies close tocutoff frequency

A81-19338Analysis of pressure spectra measurements in a

ducted combustion system[HASA-TH-81583] S81-15768

Improved methods for fan sound field determinationCHASA-CB-165188] H81-15769

BH6ISB PABISIs the engine helicopter-worthy

481-17518Turbine blade technology - Present and future

[ASHE PAPEB 80-C2/AEHO-10] A81-18639A resin injection technique for the fabrication of

aero engine composite components[PHB-90024] H81-14004

Cost/benefit analysis of advanced materialstechnologies for future aircraft turbine engines[HASA-CB-165225] H81-15006

EISIBB TESTSAdvanced transmission component development and

test program for helicoptersA81-17507

Safety considerations for helicopter drive systemsof the 1980s

A81-17510- Development and operational flight test of the

model 250-C28B gas turbine engine&81-17512

Issues regarding Army turboshaft enginesdiagnostics and condition nonitoring

A81-17514Advanced technology turboshaft IB suppression

A81-17519A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-17824The measurement and analysis of station parameters

of a turbojet engineA81-17825

EI?IBOB8BBT HAIASBBEITEnvironmental aspects of airport planning

A81-18091BBVIBOIBESt PEOTBCTIOI

Airport/environs plan making - Managing theplanning process

A81-18088EPOXI BBSIBS

A resin injection technique for the fabrication ofaero engine composite components[PHB-90024] H81-14004

EBBOB AHALISISAn optimum design procedure of total-temperature

thermocouple probesA81-17807

Geometric dilution of precision in Globalpositioning System navigation

A81-18100EBBOB COBBECTIIS DEVICES

The practical application of the Rake BlockingCorrections according to Raskell for largewind tunnel models[DS1B PAPEE 80-112] A81-19398

EBBOB SI6BALSHodel-following system with assignable error

dynamics and its application to aircraftA81-18577

ESCAPE SISTBHSPyrotechnics serving safety in aircraft air

and ground escape systemsA81-19348

ETAIOATIOBEvaluation of a computer-generated perspective

tunnel display for flight path following[HASA-TP-1736] S81-13958

Landing flying qualities evaluation criteria foraugmented aircraft[BASA-CB-163097] B81-13969

BIHAOST S1SBSAdvanced technology turboshaft IB suppression

A81-17519Exhaust gas reingestion measurements inhelicopters

A81-17521Organic compounds in the exhaust of a J85-5

turbine engine[AD-A091712] S81-13966

Exhaust noise in flight: The role of acousticinstallation effects[PBH-90029] N81-14793

A-15

EXHAUST HOSZLBS SUBJECT IIDEI

EIUOST I02ZLBSAn evaluation of wind tunnel test techniques for

aircraft nozzle afterbody testing at transonicBach numbers[AD-4091775] H81-13931

Evaluation of vind tunnel nozzle afterbody testtechniques utilizing a modern twin enginefighter geometry at Bach numbers from 0.6 to 1.2

IF-17 aircraft[AD-A0915U5] N81-13932

BIPLOSIVBSTool force evaluation of lathe machined high

explosives[HHSHP-80-20] H81-151U8

EXTEBHAL STOBESActive flutter suppression on an F-4F aircraft

with external stores using already existingcontrol surfaces[HBB-FE-17/S/PDB/20] H81-13972

Effects of nonlinearities on ving store flutter[HBB-FE-17/S/P OB/27] H81-13974

Transonic wind tunnel tests on an oscillating vingwith external store. Part 4: The wing vithunderwing: store[AD-A077370] H81-14969

An economic and versatile panel nethod foraircraft and aircraft/store configurations. Anoutline of the principal features of themathematical modeling and numericalimplementation of the British Aerospace (Barton)Hk II Panel nethod

H81-15311

F-« AIRCRAFTApplication of vector performance optimization to

a robust control loop design for a fighteraircraft[DFVLB-FB-80-14] H81-13970

Active flutter suppression on an F-4F aircraftwith external stores using already existingcontrol surfacesCHBB-FE-17/S/POB/24] H81-13972

F-15 AIBCBAFIFlight evaluation of a simplified gross thrust

calculation technique using an F I D O turbofanengine in an F-15 airplane[HASA-TP-1782] H81-15000

F-16 AIRCRAFTA case study on the F-16 fly-by-vire flight

control system BookA81-16719

F-17 AIRCRAFTEvaluation of vind tunnel nozzle afterbody test

techniques utilizing a modern tvin enginefighter geometry at Mach numbers from 0.6 to 1.2

IF-17 aircraft[AD-A091545] N81-13932

Active control of an explosive ving-store fluttercase[HBB-FE-17/S/POB/25] N81-13973

F-18 AIRCRAFTF/A-18 full scale development test

A81-16579FAIL-SAFE SISTBHS

Failure Indication and Corrective Action fortnrboshaft engines

A81-17515FAILURE BODES

Lubrication of rolling element bearingsA81-18738

FAB FIELDSPrediction of sound radiated from different

practical jet engine inlets[HASA-CB-163824] N81-14789

FATIGUE (HATEEIALS)Constant-amplitude and flight-by-flight tests on

CEBP specimens[SBB-FE-2/S/POB-26] H81-1<!006

FATIGUE TESTIHG HACBIBESControls of aeronautical structures under fatigue

testing by holographic pulsed lasersinterferometry[ISL-CO-218/79] M81-1I1300

FATIGOE TESTSFerrography as a health monitor and a design aid

for the development of helicopter gearboxesA81-18759

Constant-amplitude and flight-by-flight tests onCEBP specimens[HBB-FE-2/S/POB-26] H81-14006

The stress behavior of three advanced nickel basesuperalloys during high temperature lov cyclefatigue[AD-A091694] B81-14061

FAULT TOLBBABCEA fault tolerant multiprocessor system vithreconfiguration suitable for multiaxial flightstabilization and trimming

A81-19296Validation Nethods Besearch for Fault-TolerantAvionics and Control Systems Snb-Korking Groupneeting. CABE 3 peer reviev[HASA-CP-2167] H81-15702

FEASIBILITY AHALISISHicrovave landing systems, citations from theEngineering Index data base[PB80-814643] H81-13947

Hicrovave landing systems, citations from theBUS data base[PB80-814635] H81-13948

laser-Baman/Bayleigh flov diagnostic techniquesapplied to subsonic flov(AD-A091695] B81-14275

FEEDBACK COHTBOLHodel-folloving system vith assignable error

dynamics and its application to aircraftA81-18577

Frequency-shaped cost functionals - Extension oflinear-quadratic-Gaussian design methods

A81-18578System considerations in the implementation of

digital control[ A A S 80-032] A81-19375

Active flutter suppression on an F-I»F aircraftwith external stores using already existingcontrol surfaces[HBB-FE-17/S/PUB/24] H81-13972

FIBEB COMPOSITESHingeless tailrotor in fiber composite

construction and vibration-isolation systems/ABIS, ISIS/ for helicopters[HBB-UD-311-80-0] A81-19300

FI6BTBB AIBCBAFTCalculation of the lift dependent drag polar of

cambered fighter plane configurations vithdeflected maneuver flaps in the subsonic regionby means of a modified procedure according toLamar£ D G L B PAPEB 80-109] A81-19395

Procedures for optimal drag design of camber andflap deflection in supersonic regions vithconsideration to geonetric limits[DGLB PAPEB 80-110] A81-19396

Industry proposes supersonic ?/STOLA81-19490

Fighters for the 1990sA81-19497

Computational aerodynamic design tools andtechniques used at fighter development[HBB-FE-122/S/POB/13] N81-13950

Constant-amplitude and flight-by-flight tests onCEBP specimens[HBB-FE-2/S/PDB-26] H81-14006

FIIITB DIFFERENCE TBBOBIFinite difference computation of the steady

transonic potential flov around airplanesA81-17802

FIHTE ELEHEBT BBTHODThe method of snperelements in the dynamics of

complex structuresA81-16969

Variational principles and generalized variationalprinciples for the hybrid aerodynamic problem ofairfoil cascades on an arbitrary stream sheet ofrevolution

A81-17741Structural analysis of fuselages vith cutouts by

finite element methodA81-17816

Finite element analysis of inviscid subsonicboattail flov[HASA-TB-81650] H81-14977

FIBB PBEVEBTIOIAviation safety: Interior compartment materials

[GPO-50-388] H81-13933

A-16

SUBJECT ZBDBZ PLIGHT TESTS

Testimony of Elwood T. Driver, Vice Chairman,National Transportation Safety Board,accompanied by Gerrit J. lalhoat. Chief, HananFactors Division, and Hatthev B. BcCormick,Senior Air Safety Investigator, Hunan FactorsDivision

N81-13934Testimony of a panel consisting of: Lloyd E.Frisbee, Vice President, Engineering andOperations, Lockheed California Company; Lyle A.Wright, Director, Foverplant Engineering,Douglas Aircraft Company, acconpanied by DoctorH. C. Schjelderup, Chief Technology Engineer,Materials and process Engineering, and F. E.Duskin, Senior Design Engineer, InteriorsEngineering, Douglas Aircraft Company

N81r13937FLIGHT CHARACTERISTICS

Shipboard trials of the Quiet Short-Haul ResearchAircraft /QSHA/

A81-16581History of flight testing the L-1011 Tristar jet

transport. I - The L-1011-1A81-17976

Practical aerodynamics of the helicopter Hi-6ARussian book

181-18600The collision course: Conditions, guidance lavs

and properties[DFVLH-FB-80-06] N81-13942

FLIGHT COIDITIOISThe microburst: Common factor in recent aircraft

accidentsN81-14571

Doctor Fujita's microburst analysis at ChicagoN81-14572

FLIGHT CONTROLThe implications of current flight control

research and developmentA81-16578

A fault tolerant multiprocessor system withreconfiguration suitable for mnltiaxial flightstabilization and trimming

A81-19296System considerations in the implementation of

digital control[AAS 80-032] A81-19375

Evaluation of a computer-generated perspectivetunnel display for flight path following[NASA-TP-1736] 1181-13958

Landing flying qualities evaluation criteria foraugmented aircraft[HASA-CH-163097] N81-13969

Validation Methods Besearch for Fault-TolerantAvionics and control Systems Sub-lorking GroupMeeting. CARE 3 peer reviev[NASA-CP-2167] H81-15702

FLIGHT HAZARDSCollisions between aircraft and birds

A81-19445Aeronautical concerns and National Aeronautics and

Space Administration atmospheric electricityprojects

N81-14567FLIGHT IHSTBOHEBTS

Flight instrumentation reguirements forall-weather approach and landing

A81-18059Advanced flight deck/crew station simulator

functional requirements[NASA-CB-1593313 N81-14994

FLIGHT MECHASICSInverse problems of controlled flight dynamics -

Longitudinal motionA81-16968

PLIGHT OPERATIOISProblems of fligbt mechanics involved in

all-weather helicopter operationA81-17467

Micro-wave landing system - An operational pointof view

A81-18055B N A V benefits today - Today and future reguirements

A81-18056The introduction of S10L and BNAV to largecommercial operations

A81-18057The problems of helicopter ditching

A81-18071

FLIGHT OPTIMISATIONL-1011 Flight Management System design

considerationsA81-18074

Drag reduction through formation flight[DGLB PAPER 80-106] A81-19393

FLIGHT PATHSMidair and near midair collisions on two- and

three-dimensional curvilinear flight paths[DFVLB-FB-80-13] N81-13944

Flight evaluation of the terminal guidance system[HASA-CB-163859] H81-14991

FLIGHT SAFETIMicro-wave landing system - An operational point

of viewA81-18055

RNAV benefits today - Today and future reguirementsA81-180-56

Satellites to aid flight safety[IAF PAPEB 80-IAA-17] A81-18410

Pyrotechnics serving safety in aircraft airand ground escape systems

A81-19348Midair and near midair collisions on two- and

three-dimensional curvilinear flight pathsCDFVLB-FB-80-13] N81-13944

Measuring weather for aviation safety in the 1980's081-111568

Commuter airline safety[PB81-104267] K81-14988

Lightning. Citations from the InternationalAerospace abstracts data base[NASA-CB-163857] N81-15648

FLIGHT SIMULATIONPrediction methods for fatigue crack growth in

aircraft materialA81-18777

Evaluation of wind tunnel nozzle afterbody testtechniques utilizing a modern twin enginefighter geometry at Mach numbers from 0.6 to 1.2

YF-17 aircraft[AD-A091545] N81-13932

Development of a computer program data base of anavigation aid environment for simulated IFBflight and landing studies[HASA-TM-80064] N81-13959

Simulator study of conventional general aviationinstrument displays in path-following tasks withemphasis on pilot-induced oscillations[8ASA-TP-1776] N81-14997

Computer Generated Imagery (CGI) currenttechnology and cost measures feasibility study[AD-A091636] N81-15729

FLIGHT SIMULATORSVisual systems at Lufthansa's simulator centre

A81-19499Equipment for testing and measuring a "helmet

mounted sight and display" system with a coupledmovable television camera in theflight-simulator for research of the DFVLR[DFVLB-HITT-80-04] N81-13960

FLIGHT TESTSF/A-18 full scale development test

A81-16579Head-Op-Display flight tests

A81-16582The PZL-Sokol - New Polish helicopter

A81-17325Development and operational flight test of the

model 250-C28B gas turbine engineA81-17512

Engine-airframe transient compatibility - Analysisand test

A81-17517Exhaust gas reingestion measurements inhelicopters

A81-17521History of flight testing the L-1011 Tristar jettransport. I - The L-1011-1

A81-17976Testing model rotorcraft for overwater operations

A81-18058Circulation Control ling /CCW/ flight tests

A81-19469A status report on NASA general aviationstall/spin flight testing

A81-19471

A-17

FLOfATIOI SUBJECT IIDEI

Flight test investigation of IOBAH-C for en routenavigation in the Gulf of Bexico[AD-A091637] 881-13945

Active flutter suppression on an F-4F aircraftvith external stores using already existingcontrol surfaces[HBB-FE-17/S/POB/24] H81-13972

Constant-amplitude and flight-by-flight tests onCEBP specimens[HBB-FE-2/S/PUB-26] U81-14006

Assessment of ground effects on the propagation ofaircraft noise: The T-38A flight ezperiaent[NASA-TP-1747] 881-14788

DC-to-DC power supply for light aircraft flighttesting[NASA-CB-163850] H81-14989

FLOTATIONTesting model rotorcraft for overvater operations

A81-18058The problems of helicopter ditching

A81-18071FLOS CHABACfEBISTICS

Time dependent Navier-stokes solution of aturbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflov

H81-14964FLOB DISTOBTIOS

Steady flow past a rectangular wing irithcirculation that is variable along the span

A81-16551A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-17824Inlet flow distortion in tnrbomachinery

[ASflE PAPEB 80-GT-20] A81-17952Characteristics of the velocity field near a

ving-body combination located at an angle ofattack to an oncoming supersonic flow

A81-19337The practical application of the Hake BlockingCorrections according to Baskell for largewind tunnel models[DGLB PAPEB 80-112] A81-19398

FLOS DISTBIBDTIOHThe supercritical profile of the supercritical wing

A81-17522The measurement and analysis of station parameters

of a turbojet engineA81-17825

The coordinate-deformation method in the problemof a supersonic gas flow over an airfoildelta wings

A81-19631An investigation into grid patching technigues

881-14708FLO! BQOATIO8S

An investigation into grid patching techniques881-14708

FLOI GEOHETBIDevelopment of finite-volume methods forthree-dimensional transonic flows[AD-A090829J 881-11986

FlOB BEASOBEBEITvector and scalar characteristics of opposing jetsdischarging normally into a cross-stream

181-17997FLOW STABILITY

One-dimensional considerations concerning thestability behavior of inlet diffasers forsupersonic aircraft German thesis

A81-17548Dialogue on bridging some gaps in stability andtransition research in external, internaland free-shear layer through-flow systems

A81-18105The influence of flow disturbances on thelaminar-turbulent transition in a supersonicboundary layer

A81-19643iall cooling and the laminar-turbulent boundary

layer transition at supersonic flow velocitiesA81-196UI)

Static source locations for four nozzles aountedon a J-85 engine[HASA-CB-152401] 881-14998

TF34 engine compression system coiputer studysimulation of flow stability[SASA-CB-1598893 H81-15005

FLOB VBLOCITTVector and scalar characteristics of opposing jets

discharging normally into a cross-streamA81-17997

Analysis of unsteady pressure measurements on anaerofoil section with an harmonicallyoscillating, slotted flap[DFTLB-FB-80-22] 881-13929

FLOI TISOALIZATIOBApplication of optical methods to the study of jet

noise and turbulence[ISL-CO-201/80] H81-15819

FLUID FILBSOn the steady state and dynamic performance

characteristics of floating ring bearings[ASHE PAPEB 80-C2/L0B-17] A81-18671

Surface analysis of bearing steels after solventtreatments. II - Lubricant-coated bearing surfaces[ASLE PHEPBIHT 80-LC-8A-6] A81-18748

FLUID FLOIVortex methods for two- and three-dimensional flow

simulationsB81-15313

FLDID PBESSOBEPeriodically stiffened fluid-loaded plates. I -

Besponse to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067FLOOBOCABBOHS

Captive carry and free flight rain erosionconsiderations for reinforced ablativeflnorocarbon radome materials

A81-17453FLOTTEB

passive control of wing/store flutter[NASA-TB-81865] H81-13922

Active flutter suppression on an F-4F aircraftwith ezternal stores using already ezistingcontrol surfaces[BBB-FE-17/S/POB/24] H81-13972

Active control of an ezplosive wing-store fluttercase[MBB-FE-17/S/POB/25] S81-13973

FLDTTBB AHALISISEffects of nonlinearities on wing store flutter

[BBB-FE-17/S/POB/27] H81-13974FLT BI ilBE COHTBOL

A case study on the F-16 fly-by-wire flightcontrol system Book

A81-16719FOBCB DISTBIBDTIOI

The velocity induced by the wake of a wind turbinein a shear layer, including ground effect[FFA-TH-HO-2189-PT-3] H81-14985

Tool force evaluation of lathe machined highexplosives[BHSBP-80-20] 881-15148

FOBBBODIBSAerodynamic side-force alleviator means

[NASA -CASE-LAB- 12326-1] 881-14968FOBECASTIBG

Canada's national aviation forecasting BodelsA81-18072

Traffic forecasting for the HBIA Bew BiyadhInternational Airport

A81-18090FODIDATIOBS

Probabilistic analysis of foundation forces for aclass of unbalanced rotating machines

881-15362FOOBIBB SEBIES

A pure direct force/moment control for coaxialcounterrotating rotors

881-15007FBACT08E BECHA8ICS

Application of fracture mechanics in designinglower wing skin of transport aircraft

A81-17049FBACIDBE STRBB6TB

The effect of cyclic loading on the apparentcleavage fracture toughness of ICr-Bo-V rotorsteel

A81-17488FBBB FLIGHT

Captive carry and free flight rain erosionconsiderations for reinforced ablativefluorocarbon radome materials

A81-17453

A-18

SUBJECT ISDBX GBABS

FBBE JETSEffects of axisymmetric sonic nozzle geometry OD

Hach disk characteristicsA81-18022

FBEQOEHCI BESPOISEFrequency-shaped cost functionals - Extension of

linear-quadratic-Gaussian design methods181-18578

FBICTIOSEffects of nonlinearities on ving store flutter

[HBB-FE-17/S/POB/27] H81-1397UFDEL COHSDBPTIOI

Airline flight departure procedures - Choosingbetween noise abatement, minimum fuelconsumption and minimum cost

A81-17044Fuel conservation in the air transportation

industry - General and operational aspects181-17113

Bolls-Boyce engines status report181-17166

L-1011 Flight Kanagemeut System designconsiderations

181-18074Technological forecasting—aircraft design.

Citations from the International Aerospace database[SASl-CB-163833] K81-13957

The future of civil turbo-fan engines[PNB-90031] H81-13964

FUEL COHTAHIHATIOIThe resistance of tank protective measures to

microorganisms[SBIAS-801-551-107] H81-15072

FUEL CORBOSIOSFormation of solid phase during the heating of jet

fuels181-17372

FDEL IHJECTIOHA simple conbustor system for a small gas turbine

engine181-17503

1 vaporizing combustor vith doable combustion spaces181-17827

Fttel injector characterization studies[H1S1-CB-165200] 1181-15003

FUEL TASKSThe resistance of tank protective measures to

microorganisms[SHIAS-801-551-107] H81-1S072

FUEL TESTSComparative evaluation of the quality of jet fuels

A81-17371FOEL-AIB BATIO

Fuel injector characterization studies[H1S1-CB-165200] N81-15003

POLL SCALE TESTSF/A-18 fall scale development test

181-16579FUHCTIOiAL ABALTSIS

Frequency-shaped cost fnnctionals - Extension oflinear-guadratic-Gaussian design methods

A81-18578FOICIIOIS (BATBEBATICS)

Dual methods and approximation concepts instructural synthesis[HASl-CB-3226] H81-14347

FUSELAGESStructural analysis of fuselages Kith cutouts by

finite element method181-17816

Beduction of profile drag by blowing out throughpeg holes in areas of streamline separationbubbles[DGLB PAPEB 80-103] 181-19392

Drag estimations for stream-line and cylindricalcontour distortions on aircraft fuselages andtrain cars[DGLB PAPEB 80-116] 181-19399

SAS CBHOHITOGBIPHYOrganic compounds in the exhaust of a J85-5

turbine engine[AD-A091712] N81-13966

GAS FLO!Stationary displacement of a body by a shock wave

A81-17622

Propagation of three-dimensional acousticperturbations in channels of variablecross-sectional area at frequencies close tocutoff frequency

A81-19338Plane vortex gas flows emphasizing supersoniccase

181-19631GAS JETS

Time dependent Havier-Stokes solution of aturbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

H81-14964GAS STBEAHS

1 vaporizing combustor with double combustion spaces181-17827

GAS TOBBIHE BIGIHESCoatings in the aero gas turbine

181-17167Joint-laboratory qualification testing of oils for

gas turbine engines181-17375

A simple combustor system for a small gas turbineengine

A81-17503The digital control systei as part of anintegrated accessory fit for future engines

A81-17505Development and operational flight test of the

model 250-C28B gas turbine engine181-17512

Failure Indication and Corrective Iction forturboshaft engines

181-17515Advanced technology turboshaft IK suppression

181-17519An experimental study on kerosene-hydrogen hybrid

combustion in a gas turbine combustorA81-17841

Turbine blade technology - Present and future[ASBE PAPEB 80-C2/1EBO-10] 181-18639

Calculated and experimental data for a 118-mm boreroller bearing to 3 million DH[1SHE PAPEB 80-C2/LDB-14] A81-18668

Power control for hot gas engines[H1S1-CASE-HPO-14220-1] H81-14318

Improved capabilities to detect incipient bearingfailures[1D-1091687] H81-14325

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15425/T1] N81-11327

Gas turbine engines and transmissions for busdemonstration programsCCOO-4867-07] N81-14329

The measurement of aero gas turbine noise[PHB-90032] N81-14795

Curved centerline air intake for a gas turbineengine[H1SA-CASE-LEB-13201-1] N81-14999

Cost/benefit analysis of advanced materialstechnologies for future aircraft turbine engines[HASA-CB-165225] H81-15006

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15332/T1] N81-15414

GAS TOBBISESVector and scalar characteristics of opposing jets

discharging normally into a cross-streamA81-17997

Effects of downstream distance on turbulence decayfor the compressor research facility lowconditioning system[1D-1091543] H81-14276

Development of high-temperature turbine subsystemtechnology to a technology readiness status,phase 2[FE-1806-72] N81-14332

GAS-SOLID IHTEBFACESStationary displacement of a body by a shock wave

A81-17622GASEOUS ROCKET PBOPELLAITS

A study of air breathing rockets - Subsonic modecombustion[IAF PAPEB 80-F-270] 181-18371

GEABSWater content of helicopter gear oils

[1SME PAPEB 80-C2/DET-12] A81-18640

A-19

SBNBBAL 4VIATIOH AIBCBAFT SOBJECT IHDEI

A low height 2300 ki helicopter transmission withan enclosed planetary gear[&SHE PAPEB 80-C2/DET-17] A81-186U2

Approximation of gear transmission error bystandard gear errors[ASHE PAPEB 80-C2/DET-71] A81-18646

Experience with advanced high performance gear steelfor CH-47

[ASHE PAPEB 80-C2/DET-77] A81-18648The rigidity and performance of a simple spiral

bevel helicopter gearbox£ASBE PAPEB 80-C2/DET-103] A81-18654

Ferrography as a health monitor and a design aidfor the development of helicopter gearboxes

A81-18759Pover control for hot gas engines. [NASA-CASE-HPO-14220-1] H81-14318

GEHBBAL AVIATIOI AIBCBAFTDevelopment and certification of the Gnlfstreau III

A81-16587The Grumman Aerospace and Galfstream American

Gnlfstream III case stndy in aircraft designBook

A81-16720A status report on NASA general aviation

stall/spin flight testingA81-19471

GLASS FIBEESVanadium trineodecanoate promoter for

fiberglass-polyester soil surfacings[AD-A091785] N81-14084

SLIDERSBird flight and airplane flight instruments to

measure air currents and flight characteristics[HASA-TB-75777] N81-14962

GLOBAL POSITI01IBG SISTEH •Seometric dilution of precision in Global

Positioning System navigationA81-18100

Characteristics of NATSTAB user stationsA81-19425

GOVEBHHEHT/IHDOSTBT BELATIOSSThe federal role in airport noise control planning

A81-18073An assessment of General Aviation utilization of

advanced avionics technology[HASA-CB-159328] N81-13941

GBAPHS (CHABTS)Experimental aerodynamic characteristics of two

V/STOL fighter/attack aircraft configurations atBach numbers from 0.4 to 1.4[NASA-TB-81234] H81-14981

SBKEH FOBCTIOHA wall interference analysis in wind tunnels

A81-17472GEIDS

An investigation into grid patching techniquesK81-14708

SBOOBD BASED COHTBOLThe role of aircraft separation assurance in the

cockpitA81-18092

GBOOHD EFFECTAssessment of ground effects on the propagation of

aircraft noise: The T-38A flight experiment[HASA-TP-1747] M81-14788

The velocity induced by the wake of a wind turbinein a shear layer, including ground effect[FFA-TN-HO-2189-PT-3] H81-14985

SEODSD EFFECT (AEBODTIABICS)Determination of the effect of transverse cutouts

on the hydrodynamic characteristics of afinite-span wing in the case of steady andunsteady motion near a wall

A81-19335Experimental investigation of a right angle wing

with partially separated flow with and withoutground effects[DGLB PAPEB 80-111] A81-19397

GBOOHD EFFECT H&CHIHESHeava instabilities of amphibious air cushion

suspension systems[OTIAS-246] N81-15156

GBOOHD SOPPOBT EQOTPHERCharacteristics of NAVSTAB user stations

A81-19425Observing lightning from ground-based and airbornestations

H81-14566

GBOOHD-AIB-GBOOHD COBBDIICATIOISAutomating airborne company communications

A81-18064GBUHHAH AIBCBAFT

Development and certification of the Gulfstream IIIA81-16587

The Grumman Aerospace and Gulfstrean AmericanGalfstream III case study in aircraft designBook

A81-16720GOIDAICE SEISOBS

Low-speed wind-tunnel tests of two weathercockingsensors[DSBL-0171-TB] H81-14575

GUST LOADSAviation meteorology research and development: A

status reportH81-14557

eastsClear air turbulence: Historical comnents

B81-14562

HHABBOHIC AHALISIS

A pure direct force/moment control for coaxialcounterrotating rotors

H81-15007HABBOHIC EICITATIOS

Periodically stiffened fluid-loaded plates. I -Besponse to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067BABHOHIC OSCILLATIOH

Experimental determination of unsteady bladeelement aerodynamics in cascades. Volume 2:Translation mode cascade[NASA-CB-165166] H81-14976

HiBBIEB AIBCBAFTIndustry proposes supersonic V/STOL

A81-19490BEAD-OP DISPLAYS

Head-Op-Display flight testsA81-16582

The flying hologram - Latest in head-up displaysystems

A81-19500BEAT EXCHAHGEBS

Improved ceramic heat exchanger materialsfHASA-CB-159678] H81-14082

BEAT BESISTAHT ALLOTSBecent selected papers of Northwestern

Polytechnical University. Parts 162 BookA81-17801

The stress behavior of three advanced nickel basesnperalloys during high temperature low cyclefatigue[AD-A091694] N81-14061

BEAT TBABSFBBHind-tunnel measurements and comparison with

flight of the boundary layer and heat transferon a hollow cylinder at Bach 3[HASA-TP-1789] N81-14975

BEAVIBGHeave instabilities of amphibious air cushion

suspension systems[OTIAS-246] N81-15156

BKLICAL FLOBBotary balance data for a single-engine

agricultural airplane configuration for anangle-of-attack range of 8 deg to 90 deg[NASA-CB-3311] N81-13923

BELICOPTEB COHTBOLThe problems of helicopter ditching

A81-18071A pure direct force/moment control for coaxialcounterrotating rotors

H81-15007BELICOPTEB DBS1GH

Advanced Attack Helicopter /TAH-6U/ - status reportA81-16580

The PZL-Sokol - Hew Polish helicopterA81-17325

SNIAS helicoptersA81-19342

A-20

SUBJECT IHDEI HOgAI fOLBBASCBS

BBLICOPIBB BHGIIESSpecialists' Meeting on Helicopter PropulsionSystems, Billiamsbarg, Va., Hovenber 6-8, 1979,Technical Papers

481-17501The impact of contingency ratings on advanced

tnrboshaft engine designA81-17502

A simple conbustor system foe a small gas turbineengine

481-17503Digital control for helicopter poverplants

481-17501The T700 booster engine

481-17506Advanced transmission conponent development and

test program for helicopters481-17507

Development of helicopter transmission componentsfor the 1980s

481-17509Helicopter propulsion system development and

qualification481-17511

Development and operational flight test of themodel 250-C28B gas turbine engine

481-175124 survey of propulsion systems'malfunctions/failures resulting in helicoptermishaps

481-17513Failure Indication and Corrective Action forturboshaft engines

481-17515Review of engine/airframe/drive train dynamic

interface development problems481-17516

Engine-airframe transient compatibility - 4nalysisand test

481-17517Is the engine helicopter-worthy

481-17518HELICOPTBB PEBFOBHABCE

The XV-15 tilt rotor research aircraft481-16588

The PZL-Sokol - New Polish helicopter481-17325

Problems of flight mechanics involved inall-weather helicopter operation

48 1-17 167General Electric infrared suppressors for the

Black Hawk helicopter481-17520

Testing model rotorcraft for overwater operations481-18058

Helicopter survivability in overwater situations481-18081

Practical aerodynamics of the helicopter Hi-64Russian book

481-18600The rigidity and performance of a simple spiral

bevel helicopter'gearbox[ASME P4PEE 80-C2/DET-103] 481-18654

Petrography as a health monitor and a design aidfor the development of helicop'ter gearboxes

481-18759SNI4S helicopters

481-193*2HBLICOPTBB PBOPELLBB DRIVE

Drive system development for the 1980'shelicopter transmissions

481-17508Development of helicopter transmission components

for the 1980s481-17509

Safety considerations for helicopter drive systemsof the 1980s

481-17510Beview of engine/airframe/drive train dynamic

interface development problems481-17516

Rater content of helicopter gear oils[4SHE P4PEB 80-C2/DET-12] 481-18610

4 low height 2300 kw helicopter transmission withan enclosed planetary gear[4SHE P4PEB 80-C2/DET-17] 481-18612

Experience with advanced high performance gear steelfor CH-47

[4SHE P4PEB 80-C2/DET-77] 481-18618

Performance of computer-optimized tapered-rollerbearings to 2.1 million DB[4SHE P4PEB 80-C2/LDB-18] 481-18672

HBLICOPTEB TAIL BOTOBSHingeless tailrotor in fiber composite

construction and vibration-isolation systems/4BIS, 4SIS/ for helicoptersCBBB-OD-311-80-0] 481-19300

HELICOPTEBSHelicopter alarms - The use of A t A T incident and

accident record cards481-16689

Exhaust gas reingestion measurements inhelicopters

481-17521Helicopters - Help for the all weather terminal

481-18065The rating of helicopter noise: Development of a

proposed impulse correction[HPL-AC-93] H81-11792

HELIDH-HBOH LASBBSThe Dalembertometer

[ISL-CO-220/79] N81-11292HELflET BOOSTED DISPL4IS

Equipment for testing and measuring a "helmetmounted sight and display" system with a coupledmovable television camera in theflight-simulator for research of the DFVLB[DFVLB-HITT-80-01] H81-13960

HFB-320 AIBCB4FTSystem identification of the longitudinal motion

of the DFVLB HFB 320 research aircraft withparticular consideration of control surfaceeffectiveness[DFVLB-HITT-79-16] N81-13971

HIGH STBBHGTH STEELSBecent selected papers of Northwestern

Polytechnical University. Parts 162 BookA81-17801

HIGB TEBPBBATOBE GASESA vaporizing combustor with double combustion spaces

A81-17827Development of high-temperature turbine subsystem

technology to a technology readiness status,phase 2[FE-1806-72] H81-11332

HIGH TEHPBBATOBB IBSISThe stress behavior of three advanced nickel base

superalloys during high temperature low cyclefatigue[AD-A091691] H81-11061

HISTOGBlflSCatalog of sea state and wind speed in the South

Atlantic Bight[N4S4-CB-156872] H81-11601

HOLOGB4PHIC IBTEBFEBOBETBTControls of aeronautical structures under fatigue

testing by holographic pulsed lasersinterferometry[ISL-CO-218/79] N81-14300

HOLOGB4PHIThe flying hologram - Latest in head-up display

systems481-19500

HOBIIGThe collision course: Conditions, guidance laws

and properties[DFVLB-FB-80-06] H81-13912

HOBIXOHTAL OBIBHTATIOIThe velocity induced by the wake of a wind turbine

in a shear layer, including ground effect[FFA-TH-HU-2189-PT-3] H81-14985

HOVEBIIGHeave instabilities of amphibious air cushion

suspension systems[UTIAS-216] 881-15156

HOVEBIBG STABILITY4 pure direct force/moment control for coaxial

counterrotating rotorsH81-15007

HOHAI F4CTOBS EiGIHEEBIUG757/767 design considerations for improved

productivityA81-16581

HOHAH TOLEBAHCESAircraft annoyance evaluations using field and

laboratory simulation techniques[UTIAS-218] H81-15580

A-21

BIBBID BAVIG4TIOB SISTEHS SUBJECT ISDBI

fllBBID BAVIGATIOB StSTEHSPrinciple for the design of hybrid control systemsfor passenger transport systems

A81-17577BIDBAOLIC EQOIPHEST

Elimination of vibrations in aircraft piping systemsRussian book

481-18497BYDSODYBAHIC COEFFICIEBT5

Determination of the effect of transverse cutoutson the hydrodynamic characteristics of afinite-span ving in the case of steady andunsteady motion near a wall

A81-19335BIDBOSES EHSISES

In experimental study on kerosene-hydrogen hybridcombustion in a gas turbine combustor

481-178U1BIPEBSOHIC BODHDABI LilEB

hypersonic gas flov over a delta ving481-19632

BIPEBSOBIC FLOWin investigation of support-interference effects[NAL-TB-622] B81-14984

ICE FOBHATIOBAircraft icing instrumentation: Unfilled needs

rotary wing aircraftN81-14560

IHABB EBBABCBHEHTF-111 vindscreen machining

[Y-2232} N81-1U995IHASE PBOCESSIB6

Autonomous navigation using passively sensedterrain images

481-17977I M A G E TOBES

A new system for the study of visual informationpresentation in aeronautics - GIBI

A81-16688IHAGBBT

Computer Generated Imagery (CGI) currenttechnology and cost measures feasibility study[AD-A091636] B81-15729

IHAGIHG TECHHIQDESApplication of optical methods to the study of jet

noise and turbulence[ISL-CO-201/80] 881-15819

IHPACT DAHAGEThe effects of varhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] N81-13955

IB-FLIGST HOBITOBIiGFlight evaluation of a simplified gross thrust

calculation technique nsing an F100 turbofanengine in an F-15 airplane[8AS4-rP-1782] B81-15000

IBCOHPHESSIBLE FLOSSecond order approximation theory of an arbitrary

aerofoil in incompressible potential flovA81-17803

Nonlinear aerodynamic characteristics of a thinairfoil of arbitrary plane configuration

481-19629IBEBTIAL NAVIGATION

Cruise-missile-carriec navigation requirements481-18576

Flight test investigation of LOBAB-C for en routenavigation in the Golf of Hexico[AD-A091637] B81-13945

IBFIBITB SPAH HUGSLaminar boundary layer on svept-back vings of

infinite span at an angle of attack481-17656

1SFBASBD IfliGBBYThe flying hologram - Latest in head-up display

systemsA81-19500

IBFBABBD BADIATIOSAdvanced technology turboshaft IB suppression

A81-17519IHFB4BED IBACKIBG

General Electric infrared suppressors for theBlack Havk helicopter

A81-17520

IBGEStTOi (BH6IBBS)Exhaust gas reingestion measurements in

helicoptersA81-17521

IBJDBIESBriefs of accidents involving commuter air

carriers and on-demand air taxi operations, Q.S.General Aviation 1978[PB81-101701] 881-11987

HLBT FLOIOne-dimensional considerations concerning the

stability behavior of inlet diffusers forsupersonic aircraft German thesis

A81-17548Inlet flov distortion in tnrbonachinery

[ASHB PAPEB 80-GT-20J A81-17952Conditions of generation and methods of damping

the inlet vortex of a turbojet engineA81-19112

IILET PBESS0884 preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

481-17824IBSPBCIIOB

System for refurbishing and processing parachutesfSASA-CASE-KSC-11012-1 ] S81- 11967

IBSTBOBBBT BBBOBSAn optimum design procedure of total-temperature

thermocouple probesA81-17807

Approximation of gear transmission error bystandard gear errors

" [ASBE PAPEB 80-C2/DBT-71J A81-18646IBSTBBBEBT FLIGHT BOLES

Development of a computer program data base of anavigation aid environment for simulated IFBflight and landing studies[NASA-TH-80064] N81-13959

IBTAES SYSTEMSEffects of downstream distance on turbulence decay

for the compressor research facility lovconditioning system[AD-A091543] B81-14276

IBTEGBATED CIBCOITSDC-to-DC pover supply for light aircraft flight

testing[NASA-CB-163850] N81-14989

ISTEKBOGATIOMPerformance evaluation of an interrogation-reply

scheduling technique for a discrete addressbeacon system of radar surveillance andaircraft communication in ATC

481-19117IBVEHTOBT CO8TBOLS

Beneval function for any arbitrary period - ABayesian vay

A81-16939IBTESTBBH1S

Investment decision-makinq in international airportsA81-18079

IBTISCID FLOINonlinear aerodynamic characteristics of a thin

airfoil of arbitrary plane configurationA81-19629

An investigation into grid patching techniquesN81-11708

Finite element analysis of inviscid subsonicboattail flov[BASA-TH-81650] N81-11977

IBASDesign of the new Tehran International Airport

A81-18081

J-85 EBGIBEOrganic compounds in the exhaust of a J85-5

turbine engine[AD-A091712] B81-13966

Static source locations for four nozzles mountedon a J-85 engine[NASA-CB-152101] 881-14998

lerodynanic stability analysis of NASAJ85-13/planar pressure pulse generatorinstallation[BAS4-CB-165111] N81-15004

4-22

SUBJECT IHDBI LIGHT ilBCHAFT

JET AIBCBAFTDevelopment and certification of the Gulfstream III

A81-16587The Grumman Aerospace and Gulfstream American

Gulfstream III case stndy in aircraft designBook

A81-16720JET AIHCBAPT BOISE

Sound radiation from a finite length unflangedcircular duct with uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712Experimental investigations on shock-associated

noiseA81-17735

A study of multiple jetsA81-18024

Propagation of three-dimensional acousticperturbations in channels of variablecross-sectional area at frequencies close tocutoff frequency

A81-19338Exhaust noise in flight: The role of acoustic

installation effects[PHB-90029] N81-14793

The measurement of aero gas turbine noise[PHB-90032] N81-14795

JET BH6IHE FUELSComparative evaluation of the quality of jet fuels

A81-17371Formation of solid phase during the heating of jet

fuelsA81-17372

JET BNGISESAn evaluation of wind tunnel test techniques for

aircraft nozzle afterbody testing at transonicHach numbers[AD-A091775] H81-13931

Prediction of sound radiated from differentpractical jet engine inlets[HASA-CR-163824] N81-14789

JET BIBAOSTVector and scalar characteristics of opposing jets

discharging normally into a cross-streamA81-17997

Organic compounds in the exhaust of a J85-5turbine engine[AD-A091712] N81-13966

JET FLO»Static source locations for four nozzles mounted

on a J-85 engine[NASA-CH-152M01 ] HB1-14998

JET TBBOSTFlight evaluation of a simplified gross thrust

calculation technique using an F100 turbofanengine in an F-15 airplane[NASA-TP-1782] H81-15000

JOINTS (JOHCTIOIS)Sealing joints and cracks, thin resurfacing, and

locating voids under concrete slabs[PB80-21563S] B81-14182

JOOBBAL BEABIiGSOn the steady state and dynamic performance

characteristics of floating ring bearings[ASME PAPEB 80-C2/LUB-17] A81-18671

Dynamic characteristics of a high-speed rotor withradial and axial foil-bearing supports[ A S M E PAPEB 80-C2/1UB-35] A81-18683

KKEBOSEHE

An experimental study on kerosene-hydrogen hybridcombustion in a gas turbine combustor

A81-17841

L-1011 AIBCBAFTAir traffic management enhancement through newavionics /4-D/

A81-16583History of flight testing the L-1011 Tristar jet

transport. I - The L-1011-1A81-17976

L-1011 Flight Management System designconsiderations

A81-18074

LAST BAB BOUBDABT LATEBLaminar boundary layer on svept-back wings of

infinite span at an angle of attackA81-17656

The influence of flow disturbances on thelaminar-turbulent transition in a supersonicboundary layer

A81-19643LAHIHAB FLOi

Dialogue on bridging some gaps in stability andtransition research in external, internaland free-shear layer through-flow systems

A81-18105Laminar-airfoils for transport aircraft

[ DFVLB-MITT-80-07] H81-13952LAHINATES

The matrix analysis of wingsA81-17818

LAHD DSEInvestment decision-making in international airports

A81-18079LAIDING AIDS

Airport visual approach, guidance and landingsystems - Airline pilots viewpoint

A81-18083LAHDIHG GBAB

Today and the fatare in aircraft wheel and brakedevelopment

A81-170U6Stress measurements on landing gear for the Airbus

A-300 B2A81-19299

LASEB DOPPLEB VELOCIHETEBSA computer-based laser Doppler velocimeter

[DFVLB-HITT-79-14] 1181-14289LASEB IHTBHFEHOHETBI

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] H81-14300

LATEBAl COHTBOLSimulator study of conventional general aviation

instrument displays in path-following tasks withemphasis on pilot-induced oscillations[HASA-TP-1776] B81-14997

LATEBAL STABILITYLeading-edge deflection optimization for a highly

swept arrow wing configuration[HASA-TP-1777] H81-14974

LATHESTool force evaluation of lathe machined high

explosives[HHSMP-80-20] N81-15148

LEADIHG EDGESExperimental study of supersonic viscous leeside

flow over a slender delta wing[8ASA-TM-81248] N81-14265

Leading-edge deflection optimization for a highlyswept arrow wing configuration[HASA-TP-1777] 881-14974

LIFT AOGHEBTATIOBCirculation control Wing /CCW/ flight tests

A81-19469Downwash calculation at close range behind a

trapezoidal wing in supersonic flow[FFA-TH-AD-1661] 881-13925

LIFT DBAS BATIOCalculation of the lift dependent drag polar of

cambered fighter plane configurations withdeflected maneuver flaps in the subsonic regionby means of a modified procedure according toLamar[ DGLB PAPEB 80-109] A81-19395

LIFTING BODIESThe effects of warhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] N81-13955

LIFTING BOTOBSRind-tunnel test of an articulated helicopter

rotor model with several tip shapes[NASA-TH-80080] B81-13918

LIGHT AIBCBAFTA status report on NASA general aviation

stall/spin flight testingA81-19471

A-23

LIGBTHIH6 SUBJECT IBDBX

LISHTSIS6Observing lightning from ground-based and airborne

stationsH81-11566

Aeronautical concerns and National Aeronautics andSpace Administration atmospheric electricityprojects

H81-14567Lightning, citations from the International

Aerospace abstracts data base[NiSA-CB-163857] N81-15648

LIGHTSIIG SOPPBBSSIOIA case study on the P-16 fly-by-wire flight

control system Book481-16719

LIBIHGSThe near of PTPE-containing dry bearing liners

contaminated by fluids[ASLE PBEPBINT 80-LC-6B-3] A81-18758

LOAD TESTSPerformance of computer-optimized tapered-roller

bearings to 2.4 million ON[ASHE PAPEB 80-C2/LUB-18] A81-18672

LOADS (FOBCES)Probabilistic analysis of foundation forces for a

class of unbalanced rotating machinesN81-15362

LOHGITUDIBiL COBTBOLLanding flying gualities evaluation criteria for

augmented aircraft[NASA-CB-163097] N81-13969

Application of vector performance optimization toa robust control loop desiga for a fighteraircraft[DFVLB-FB-80-14] N81-13970

System identification of the longitudinal motionof the DFVL8 HFB 320 research aircraft withparticular consideration of control surfaceeffectiveness[DFVLB-MITT-79-16] N81-13971

LOHABOmega - An economic Loran A replacement

A81-18077LOBAB C

Flight test investigation of LOBAS-C for en routenavigation in the Gulf of Mexico[AD-A091637] N81-13945

DC-to-DC power supply for light aircraft flighttesting[NASA-CB-163850] N81-14989

LOB SPEEDA computer program for the design and analysis of

low-speed airfoils, supplement[NASA-TH-81862 ] N81-13921

LUBRICANT TESTSJoint-laboratory gualification testing of oils for

gas turbine enginesA81-17375

Lubrication of rolling element bearingsA81-18738

LUBRICATING OILSComposition of sludge formed in B-3V oil

A81-17373Joint-laboratory qualification testing of oils for

gas turbine enginesA81-17375

Hater content of helicopter gear oils[ A S H E PAPEB 80-C2/DET-12] A81-18640

Surface analysis of bearing steels after solventtreatments. II - Lubricant-coated bearing surfaces[ASLE PB2PBINT 80-LC-8A-6] A81-18748

LUBRICATIONLubrication of rolling element bearings

A81-18738

MHACB CO1ES

Hypersonic gas flow over a delta wingA81-19632

N81-14292

HACH-ZEBNDEB IBTERFEBOHBTEBSThe Dalembertometer

[ISL-CO-220/79]HACBISIHG

F-111 windscreen machining[Y-2232] N81-14995

Tool force evaluation of lathe aachined highexplosives[MHSMP-80-20] N81-15148

HAIHTEHASCESystem for refurbishing and processing parachutes[BASA-CASE-KSC-11012-1] B81-14967

HAS MACHISE STSTEMSA cockpit view of advanced airline avionics

A81-16585A new system for the study of visual information

presentation in aeronautics - GIBIA81-16688

Coupater generated displays and pilot effectivenessA81-18082

HAB46BBBHT PLASBIBGMicrowave landing systems. Citations from the

Engineering Index data base[PB80-814643] N81-13947

Hicrowave landing systems. Citations froa theNTIS data baseCPB80-81463S] K81-13948

HAIAGEBBHT SYSTEMSL-1011 Flight Management System design

considerationsA81-18074

Bodeling of the terminal area Air TrafficManagement and Control

A81-18085Bunway Configuration Management System concepts

A81-18089HABKOVBBABILITI

The collision course: Conditions, guidance lawsand properties[DFVLB-FB-80-06] N81-13942

Theoretical investigation of the influence ofspoiler dynamics on the handling qualities of anaircraft with direct lift control[DFVLB-FB-80-07] H81-13975

A pure direct force/moment control for coaxialcounterrotating rotors

N81-15007HAPPING

Sap-type displays for air navigationA81-19««3

BABITIBE SATELLITESAeronautical-Maritime Engineering satellite /AMES/

program of Japan[IAF PAPEB 80-D-171] A81-18318

BASS SPECTBOSCOPTOrganic compounds in the exhaust of a J8S-S

turbine engine[AD-A091712] N81-13966

HATBBIALS TESTSNondestructive dynamic testing

A81-19657MATHEMATICAL MODELS

i contribution to stabilization of flight vehicleparachute systems[DF7LB-HITT-80-05] N81-13926

Service life determination for the DH-60-A (OTTAS)helicopter elastomeric bearings[AD-A0917S6] N81-11321

An analytic model of subsonic flow around anairflow with a spoiler

B81-14966HATBICES (MATHEMATICS)

Grid generation for general three-diaensionalconfigurations

N81-14714HACBIX METHODS

The automatic matrix force method and techniquesfor handling more complex computations withgiven computer capacity

A81-17815Structural analysis of fuselages with cutouts by

finite element methodA81-17816

The matrix analysis of wingsA81-17818

HAI1BOH LIKELIHOOD ESTIMATESSystem identification of the longitudinal notion

of the DFTLB HFB 320 research aircraft withparticular consideration of control surfaceeffectiveness[DFVLB-MITT-79-16] S81-13971

METAL COATINGSCoatings in the aero gas turbine

A81-17167Prevention of spline waar by soft metallic coatings

aircraft engines[AD-A091861] N81-14064

A-2»

SUBJECT IBDBI NAVIGATIOI AIDS

HBT1L F1TISOEThe effect of cyclic loading on the apparentcleavage fracture toughness of 1Cr-Ho-v rotorsteel

181-17*88Prediction methods for fatigue crack growth in

aircraft materialA81-18777

HBTAL SOBFACESSurface analysis of bearing steels after solvent

treatments. II - lubricant-coated bearing surfaces[ASLE PBEPBINT 80-LC-8A-6] A81-18748

Surface finishing[HASA-CASB-MSC-12631-3] N81-14077

BBTALLOGBAPBYFerrography as a health nonitor and a design aid

for the development of helicopter gearboxesA81-18759

HETBOBOLOGICAL JiSTBUHBNTSSurvey of Hotkshops on Meteorological and

Environmental Inputs to Aviation SystemsN81-14556

Hinds and wind shear in-situ sensorsN81-14563

Bird flight and airplane flight instruments tomeasure air currents and flight characteristics[NASA-TM-75777] N81-14962

BETEOEOL06ICAL PABABETBBSProceedings: Fourth Annual Horkshop on

Heteorological and Environmental Inputs toAviation systems[UASA-CP-2139] N81-14555

Survey of Bookshops on Meteorological andEnvironmental Inputs to Aviation Systems

N81-14556Aviation meteorology research and development: A

status reportH81-14557

Federal Aviation Administration and NationalHeather Service Aviation Research and Development

N81-14558Aircraft icing instrumentation: Unfilled needs

rotary wing aircraftH81-14560

BETBOBO1OGICAL SEHVICESAn assessment of General Aviation utilization of

advanced avionics technology[NASA-CR-159328] N81-13941

Measuring weather for aviation safety in the 1980's1181-14568

BICBOOBGAHSBSThe resistance of tank protective measures to

microorganisms[SNIAS-801-551-107] H81-15072

BICBOWAVE LABDIK6 SYSTEMSInternational Air Transportation Conference, New

Orleans, la., April 30-Hay 3, 1979, Proceedings.Volumes 1 & 2

481-18051Micro-wave landing system - An operational point

of viewA81-18055

The importance of 'Interim Standard MicrowaveLanding System1 for small community airports

A81-18087Microwave landing systems. Citations from the

Engineering Index data base[PB80-814643] B81-13947

Microwave landing systems. Citations from theNTIS data base[PB 80-8 14635] H81-13948

HIOAIB COLLISIONSMidair and near midair collisions on two- and

three-dimensional curvilinear flight paths[DFV1B-FB-80-13J B81-13944

MILITABI AIB FACILITIESSouthern California aviation system study

[PB 80-2 15544] N81-13916MILITARY AIBCBAFT

The implications of current flight controlresearch and development

A81-16578Optimum selection of main parameters for the

reverse design of a supersonic military aircraftA81-17047

Cruise-missile-carrier navigation reguirementsA81-18576

Design to cost and new technologiesA81-19347

Solid-state power system use expandsA81-19491

Primary training of military pilots - Changingtheories and new trainers

A81-19498MILITABI A7IATIOB

Pyrotechnics serving safety in aircraft airand ground escape systems

A81-19348Aircraft maintenance. Citations from the

International Aerospace Abstracts data base[NASA-CB-163837] N81-13917

HIIITABI BE1ICOETEBSHelicopter propulsion system development and

gualificationA81-17511

Issues regarding Army turboshaft enginesdiagnostics and condition monitoring

A81-17514MILITABI OPEBATIOHS

Planning for and evaluating the potential of aland based aircraft for carrier operations

A81-19470MIIITABI TBCBHOLOGT

Advanced Attack Belicopter /IAH-64/ - status reportA81-16580

Head-Op-Display flight testsA81-16582

BISS DISTAHCEThe collision coarse: Conditions, guidance lawsand properties[ DFVLB-FB-80-06] S81-13942

MISSILE COBTBOLThe collision course: Conditions, guidance lawsand properties[DFV1B-FB-80-06] N81-13942

•ISSUE DEFENSEGeneral Electric infrared suppressors for theBlack Hawk helicopter

A81-17520HISSILE LADBCHEBS

Cruise-aissile-carrier navigation reguirementsA81-18576

BODAL BESPOISEImproved methods for fan sound field determination[NASA-CB-165188] S81-15769

BOISTOBE CONTBNTHater content of helicopter gear oils[ASME PAPER 80-C2/DET-12] A81-18640

MOTIBG IAEGET IBDICATOBSDetection of moving objects Bnssian book

A81-18773HOLTIPBOCESSING (COHPOTEBS)

A fault tolerant multiprocessor system withreconfiguration suitable for multiaxial flightstabilization and trimming

A81-19296

NBASA PBOGRAHS

Shipboard trials of -the Quiet Short-Haul BesearchAircraft /QSBA/

A81-16581A status report on NASA general aviationstall/spin flight testing

A81-19471•ATIOBAL AVIATION STSTEB

Canada's national aviation forecasting modelsA81-18072

IAVIEB-STOKES EQUATIONTime dependent Bavier-Stokes solution of aturbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

N81-14964IAVIGATION AIDS

International Air Transportation Conference, NewOrleans, la., April 30-Hay 3, 1979, Proceedings.Volumes 162

A81-18051Omega - An economic loran A replacement

A81-18077Hap-type displays for air navigation

A81-19443Development of a computer program data base of a

navigation aid environment for simulated IFBflight and landing studies[NASA-TM-80064] N81-13959

A-25

BAVI6ATIOH IISTBOHEBTS SOBJECT IIDEI

HAVIGATIOH INSTBOMEITSBadio navigation for aircraft: Handbook

Bussian bookA81-18599

A81-18410

NAVIGATION SATELLITESSatellites to aid flight safety

[ IAF PAPEB 80-IAA-17JNAVSTAB SATELLITES

Geometric dilation of precision in GlobalPositioning System navigation

A81-18100Characteristics of BAVSTAB user stations

A81-19425NICKEL ALLOTS

The stress behavior of three advanced nickel basesuperalloys daring high temperature low cyclefatigae[AD-A091694] N81-14061

SIGHT FLIGHTS (AIBCBAFT)The flying hologram - Latest in head-up display

systemsA81-19500

BOISE (SOtJND)The Dalembertometer

[ISL-CO-220/79] N81-14292NOISE HEASOBEHEHT

Experimental investigations on shock-associatednoise

A81-17735The me&sarement of aero gas tarbine noise

[PBB-90032] N81-14795BOISE POLLOTIOI

Maneuvering aircraft: Boise pollution andcontrol. Citations froa the HTIS data baseIPB80-815566] N81-14525

HOISE PBEDICTIOH (AIBCBAFT)Prediction of sound radiated from different

practical jet engine inlets[NASA-CB-163824] N81-14789

BOISE PBOPAGATIOIAssessment of ground effects on the propagation of

aircraft noise: The T-38A flight experiment[NASA-TP-1747] H81-14788

Noise and noise abatement in fans and blovers: Areview[DFVlK-FB-80-16] H81-14796

Static source locations for four nozzles mountedon a j-85 engine[BASA-CB-152401] N81-14998

NOISE SEDUCTIONAirline flight departure procedures - Choosing

between noise abatement, minimam fuelconsumption and min imum cost

A81-17044A study of multiple jets

A81-18024The federal role in airport noise control planning

A81-18073Technological forecasting—aircraft design.

Citations fron the International Aerospace database[NASA-CB-163833] N81-13957

Noise and noise abatement in fans and blowers: Areview[DFVlB-PB-80-16] N81-14796

Carved centerline air intake for a gas turbineengine[BASA-CASE-LEU-13201-1] N81-14999

HOISE SPECTBAExperitoental investigations on shock-associated

noiseA81-17735

A study of multiple jetsA81-18024

Analysis of pressure spectra measurements in aducted combustion systea[BASA-TH-81583] N81-15768

NOISE TOLEBABCEThe annoyance caused by noise around airports

[NAS4-TM-75784] N81-15579BOHDESTBOCTIVE TEStS

Bon-destructive pavement evaluationA81-18062

Becent developments in NDT techniques forairport pavement testing

A81-18078Nondestructive dynamic testing

A81-19657

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] N81-14300

IOIFLAHSABLB MATERIALSAviation safety: Interior compartment materials[GPO-50-388] N81-13933

Testimony of James J. Kramer, AssociateAdministrator for Aeronautics and SpaceTechnology, National Aeronautics and SpaceAdministration, accompanied by John H. Enders,Project Manager, Aviation Safety TechnologyOffice, John A. Parker, Chemical BesearchProjects Office, NASA-Ames Besearch Center, andOemitrins A. Kourtides, Chemical BesearchProjects Office, NASA-AMES Besearch Center

H81-13935Testimony of Bichard R. Taylor, Vice President and

Special Assistant to the President, and EugeneA. Bara, Chief Engineer, Payloads Systems,Boeing Commercial Airplane Company

N81-13936Testimony of a panel consisting of: Lloyd E.Frisbee, Vice President, Engineering andOperations, Lockheed California Company; Lyle A.(right. Director, Powerplant Engineering,Douglas Aircraft Company, accompanied by DoctorH. C. Schjelderup, Chief Technology Engineer,Materials and Process Engineering, and F. E.Duskin, Senior Design Engineer, InteriorsEngineering, Douglas Aircraft company

B81-13937BOBLINB1B STSTEHS

Application of the MNA design method to anonlinear turbofan engine multivariableHyquist array method[NASA-CB-163855] N81-15001

NOSLIBEABITIEffects of nonlinearities on wing store flutter[MBB-FE-17/S/PUB/27] N81-13974

IOZZLE DESIGNOne-dimensional considerations concerning thestability behavior of inlet diffusers forsupersonic aircraft German thesis

A81-17548Investigation of convergent-divergent nozzles

applicable to reduced-power supersonic cruiseaircraft[NASA-TP-1766] B81-14972

NOZZLE FLO!Effects of azisymmetric sonic nozzle geometry on

aach disk characteristicsA81-18022

A study of multiple jetsA81-18024

NOZZLE 6EOMETBIEffects of axisymmetric sonic nozzle geometry on

Mach disk characteristicsA81-18022

Static source locations for four nozzles mountedon a J-85 engine[SASA-CB-152401] B81-14998

NOHBBICAL ANALYSISThe automatic matrix force method and techniques

for handling more complex computations withgiven computer capacity

A81-17815Dual methods and approximation concepts in

structural synthesis[BASA-CB-3226] B81-14347

HDIBBICAL CONTBOLDigital control for helicopter powerplants

A81-17504•OHEBICAL FLO! VISUALIZATION

An analytic model of subsonic flow around anairflow with a spoiler

N81-14966BIQOIST DIAGBAH

Application of the HNA design method to anonlinear turbofan engine multivariableByguist array method[NASA-CB-163855] B81-15001

OIL ADDITIVESComposition of sludge formed in B-3V oil

A81-17373

A-26

SUBJECT IHDBZ PILOT PEHFOBHABCE

OMEGA BAVIGATI08 SYSTEHOmega - An economic Loraa A replacement

OiBOABD EQOIPHEBTSurvey of Workshops on Heteorological and

Environmental Inputs to Aviation Systems

Kinds and Hind shear in-situ sensors

A81-18077

N81-14556

H81-11I563OPEBATIOHil PBOBLEHS

Problems of flight mechanics involved inall-weather helicopter operation

A81-17467OPTICAL HEASOBIHS IHSTBOHEHtS

Application of optical methods to the study of jetnoise and turbulence[ISL-CO-201/80] H81-15819

OPTIOAL COITBOLHodel-folloving system with assignable error

dynamics and its application to aircraftiBI-18577

Frequency-shaped cost functionals - Extension oflinear-quadratic-Gaussian design methods

A81-18578OPTIHIZATIOI

Some aspects of optimizing the aerodynamics ofturbine stages

A81-19325Computational aerodynamic design tools and

techniques used at fighter development[MBB-FE-122/S/POB/13] N81-13950

fundamentals of conceptual design optimization ofsubsonic transport aircraft[VTH-LB-292] H81-13951

Economic evaluation of flying-qualities designcriteria for a transport configured with relaxedstatic stability[HASA-TP-1760] N81-13968

Application of vector performance optimization toa robust control loop design for a fighteraircraft[DFVLB-FB-80-14] N81-13970

Dual methods and approximation concepts instructural synthesis[NASA-CB-3226] N81-14347

OBSAHIC COHPOOMDSOrganic compounds in the exhaust of a J85-5

turbine engine[AD-A091712] N81-13966

OBOGBAPHIExperimental investigation of orographic naves and

vertical motions in the Krasnovodsk airport area481-19441

OSCILLATIOSSSimulator study of conventional general aviation

instrument displays in path-following tasks withemphasis on pilot-induced oscillations[NAS4-TP-1776] S81-14997

OXIDATIONFormation of solid phase during the heating of jet

fuelsA81-17372

OIIDATIOB BESISTAICEJoint-laboratory qualification testing of oils for

gas turbine engines481-17375

PANEL BBTBOD (FLUID DIHAHICS)Solution of plane cascade flov using improved

surface singularity methods application ofpanel method to internal aerodynamics[NASA-TH-81589] 881-14979

PARACHUTE FABRICSSystem for refurbishing and processing parachutes

[NASA-CASE-KSC-11042-1] N81-14967PABACBOTBS

System for refurbishing and processing parachutes[NASA-CASE-KSC-11042-1] B81-14967

PABABETBB IDENTIFICATIONTheoretical investigation of the influence of

spoiler dynamics on the handling qualities of anaircraft with direct lift control[DFVLB-FB-80-07] N81-13975

PABAHETEBIZATIOHEconomic evaluation of flying-qualities design

criteria for a transport configured with relaxedstatic stability[HASA-TP-1760] N81-13968

PASSBSGEB ilBCBiPfA case study in aircraft design: The de Havilland

family of Slot commuter aircraft BookA81-16717

Principle for the design of hybrid control systemsfor passenger transport systems

A81-17577The introduction of STOL and BHAV to large

commercial operationsA81-18057

Canada's national aviation forecasting models481-18072

The role of aircraft separation assurance in thecockpit

A81-18092PATHOLOGY

The annoyance caused by noise around airports[HASA-TH-75784] N81-15579

PAVBHEHTSIntroduction to a rigid pavement design procedure

A31-18054Non-destructive pavement evaluation

481-18062Prestressed concrete airfield pavements

A81-18063Runway rehabilitation, Washington National Airport

481-18066Fully bonded concrete overlay for an airport runway •

A81-18075OK pavement design and evaluation - A new approach

A81-18076Recent developments in HOT techniques for

airport pavement testingA81-18078

Sealing joints and cracks, thin resurfacing, andlocating voids under concrete slabs[PB80-215635] N81-14182

PEBFOBBAICE PBBDICTIO1A case study in aircraft design: The de Havilland

family of STOL commuter aircraft BookA81-16717

Non-destructive pavement evaluationA81-18062

The rigidity and performance of a simple spiral" bevel helicopter gearbox

[ASHE PAPEB 80-C2/DET-103] 481-18654Prediction methods for fatigue crack growth in

aircraft material481-18777

PBBFOBHANCE TBSISStatistical relationship between median visibility

and conditions of worstcase nanmade impact onvisibility[L4-DB-80-2485] N81-14550

Investigation of convergent-divergent nozzlesapplicable to reduced-power supersonic cruiseaircraft[NASA-IP-1766] N81-14972

PEBIPBEBAL JET FLOBDownwash calculation at close range behind a

trapezoidal wing in supersonic flow[PFA-TN-AO-1661] N81-13925

PEBTUBBATION THEOBISecond order approximation theory of an arbitrary

aerofoil in incompressible potential flowA81-17803

PHOTOGBAPHIC BQDIPBBBTBird flight and airplane flight instruments to

measure air currents and flight characteristics[NASA-TH-75777] N81-14962

PHYSIOLOGICAL EFFECTSThe annoyance caused by noise around airports

[NASA-TB-75784] N81-15579PILOT PEBFOBHAHCB

Avionics and displays in a future airspace system481-18070

Computer generated displays and pilot effectiveness481-18082

Airport visual approach, guidance and landingsystems - Airline pilots viewpoint

481-18083Evaluation of a computer-generated perspective

tunnel display for flight path following[N4SA-TP-1736] N81-13958

A-27

PILOT TBAIHIIG SOBJECT IBDEI

Simulator study of conventional general aviationinstrument displays in path-following tasks withemphasis on pilot-induced oscillations[8ASA-TP-1776] B81-14997

PILOT TBAIBIB6Primary training of military pilots - Changing

theories and nev trainers181-19498

Visual systems at Lufthansa's simulator centre481-19*99

PIPES (TUBES)Elimination of vibrations in aircraft piping systems

Russian book481-18497

PISIOH EB6IHESAdvanced Technology Spark-Ignition Aircraft Piston

Engine Design Study[B4S4-CB-165162] H81-13963

PISTOISPower control for hot gas engines

[BASA-CASB-BPO-14220-1] N81-14318PITCH (IHCLIBATIOI)

Landing flying' qualities evaluation criteria foraugmented aircraft[BASA-CB-163097] H81-13969

PITC8IHG BOBEHTSProbabilistic analysis of foundation forces for a

class of unbalanced rotating machinesB81-15 362

PLENOfl CB1BBEBSThe resonance frequencies of ventilated wind tunnels

[ABC-B/li-3841] B81-15009POLLUTIOB COBTBOL

The federal role in airport noise control planningA81-18073

Maneuvering aircraft: Boise pollution andcontrol. Citations from the HTIS data base[PB80-815566] H81-14525

POLTHBB BATBIX COHPOSITE HATEBIALSCaptive carry and free flight rain erosion

considerations for reinforced ablativefluorocarfaon radome materials

481-17153POLIHEBIC FILBS

Surface finishing[N4S4-C4SE-HSC-12631-3] B81-11077

POLITETB4FLDOBOETHTLEBEThe wear of PTFE-containing dry bearing liners

contaminated by fluids[ASLE PBEPHIBT 80-LC-6B-3] A81-18758

POTEBTIAL FLO!Becent selected papers of Borthwestern

Polytechnical Oniversity. Parts 162 BookA81-17801

Finite difference computation of the steadytransonic potential flow around airplanes

A81-17802Second order approximation theory of an arbitrary

aerofoil in incompressible potential flowA81-17803

Aerodynamic calculations and design of subcriticalaerofoils

A81-17801POBEB EFFICIEHCI

Some aspects of optimizing the aerodynamics ofturbine stages

A81-19325PBECIPIIATIOB (CHEHISTBT)

Composition of slndge formed in B-3V oil481-17373

PBEDICTIOB ABALISIS TECBHIQOESService life determination for the DH-60-A (UTTAS)helicopter elastomeric bearingsC4D-4091756] B81-11324

PEESSOBB DISTBIBOTIOBSome characteristics of subsonic flow over theroot area of a sweptback wing

481-19633Analysis of unsteady pressure measurements on an

aerofoil section with an harmonicallyoscillating, slotted flap[DFVLB-FB-80-22] B81-13929

Transonic wind tunnel tests on an oscillating wingwith external store. Part 1: The wing withunderwing: Store[4D-4077370] B81-14969

An investigation of support-interference effects[ BAL-TB-622 ] B81-11981

PBEESDBB OSCILLATIOBSAnalysis of unsteady pressure measurements on an

aerofoil section with an harmonicallyoscillating, slotted flap[DF7LB-FB-80-22] B81-13929

PBESTBESSISSPrestressed concrete airfield pavements

A81-18063PBODDCT DEVBLOPBBBT

The Grumman Aerospace and Gulfstream AmericanGulfstream III case study in aircraft designBook

481-16720The design-to-cost of aircraft

481-19344Development of high-temperature turbine subsystem

technology to a technology readiness status,phase 2[FE-1806-72] B81-14332

PBODDCTIOfl COSTSAircraft engine programs employing cost objectives

481-19316PBODUCTIOB ESGIBEBBIBS

Design to cost and new technologiesA81-19347

PEOPELLAHT COHBOSTIOSA study of air breathing rockets - Subsonic mode

combustion[ I A F PAPEB 80-F-270] A81-18371

PBOPELLABT EIPLOSIOBSTestimony of Elwood T. Driver, Vice Chairman,

Bational Transportation Safety Board,accompanied by Gerrit J. Valhout, Chief, HumanFactors Division, and Batthew B. BcCormick,Senior Air Safety Investigator, Human FactorsDivision

B81-1393UPBOPBLLEB EFFICIEHCI

Aerodynamic design of a ducted propeller -Optimization of efficiency

481-17146Calculation of propeller efficiency for an idealpropeller

A81-19444PBOPOLSIOB

Bibliography of Supersonic Cruise Besearch (SCB)program from 1977 to mid-1980[BASA-BP-1063] B81-14973

PBOPOLSIOB SISTEB COBFI60BATIOHSAdvanced Technology Spark-Ignition Aircraft Piston

Engine Design Study[B4S4-CB-165162] B81-13963

Experimental analysis and methods to determine thedynamic behavior of propulsion shafting systems

B81-15401PBOPOLSIOB SISTEB PEBFOBMABCE

Specialists' Beeting on Helicopter PropulsionSystems, Hilliamsbnrg, Va., Bovember 6-8, 1979,Technical Papers

A81-17501Helicopter propulsion system development and

qualification481-17511

A survey of propulsion systems'malfunctions/failures resulting in helicoptermishaps

A81-17513PBOPOLSIVE EFFICIBBCT

The impact of contingency ratings on advancedturboshaft engine design

A81-17502PBOTECTIVE COATIB6S

Coatings in the aero gas turbineA81-17167

The resistance of tank protective measures tomicroorganisms[SBIAS-801-551-107] B81-15072

PBOTOBBB4BCESAn investigation of support-interference effects

[B4L-TB-622] B81-14984PULSED L4SEBS

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] H81-14300

PTBOTECHBICSPyrotechnics serving safety in aircraft air

and ground escape systems481-19348

4-28

SUBJECT IIDBI BIB6 STBOCIOBBS

Q01LITI COBTBOLCoaparative evaluation of the quality of jet fuels

481-17371Automatization of the adhesion process for

supporting airframe parts in light contour systemsA81-19297

RADAB B A TIG AII01Hidair and near midair collisions on tvo- and

three-dimensional curvilinear flight paths[DFVLH-FB-80-13] H81-13944

BADIATIOB SHIELDINGGeneral Electric infrared suppressors for the

Black Hawk helicopterA81-17520

BADIO COHHUBICATIOBAeronautical-Haritime Engineering Satellite /AHES/

program of Japan[IAF PAPER 80-D-171] A81-18318

BAPIO COITBOLAerial surveying of small areas from a small

remotely controlled droneA81-17525

BADIO BATIGATIOBOmega - An economic Loran A replacement

A81-18077Radio navigation for aircraft: Handbook

Eussiao bookA81-18599

BADOBB BATEBIALSCaptive carry and free flight rain erosion

considerations for reinforced ablativefluorocarbon radoae materials

A81-17453RAIL TBABSPORTATIOI

Drag estimations for stream-line and cylindricalcontour distortions on aircraft fuselages andtrain cars[DGLB PAPER 80-116] A81-19399

BAIH BBOSIOICaptive carry and free flight rain erosion

considerations for reinforced ablativefluorocarbon radome materials

A81-17453BAIIAB SPECTBA

Laser-Baman/Rayleigh flow diagnostic techniquesapplied to subsonic flow[AD-A091695] H81-14275

BASDOH PBOCESSBSDetection of moving objects Russian book

A81-18773RAT TRACIHG

Volumetric pattern prediction of antennas onaircraft using the geometrical theory ofdiffraction[DFVLR-FB-80-01 ] H81-1M95

B4ILEI6H SCATTEBIBGLaser-Baxan/Bayleigh flow diagnostic techniques

applied to subsonic flowCAD-A091695] B81-11I275

BECTABGDLAB HUGSSteady flow past a rectangular ling with

circulation that is variable along the spanA81-16551

Determination of the effect of transverse cutoutson the hydrodynamic characteristics of afinite-span wing in the case of steady andunsteady motion near a wall

A81-19335Experimental investigation of a right angle wing

with partially separated flow with and withoutground effectsC D G L R PAPER 80-111] A81-19397

BBDOBDABT COHPOBEBTSThe automatic matrix force method and technigues

for handling more complex computations withgiven computer capacity

A81-17815BEFLECIBD BAVBS

Exhaust noise in flight: The role of acousticinstallation effects[PHR-90029] H81-14793

BEGIOHAL PLABIIiGEnvironmental aspects of airport planning

A81-18091BBIBFOBCED PLASTICS

Vanadium trineodecanoate promoter forfiberglass-polyester soil snrfacings[AD-A091785] H81-14084

BBIBFOBCBD PLATESPeriodically stiffened fluid-loaded plates. I -

Response to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067RELIABILITY ABALISIS

iind shear systems integration plan, TICOB (visualconfirmation) reliability analysis[PB80-218233] B81-13949

Validation Methods Research for Fault-TolerantAvionics and Control Systens Sub-Working GroupHeeting. CASE 3 peer review[BASA-CP-2167] B81-15702

BELIABILITI EB6IIBEBHGStress measurements on landing gear for the Airbus

A-300 B2A81-19299

An investigation of safety hazards and reliabilityproblems in aerial refueling stores[AD-A091788] B81-13938

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15332/T1] B81-15414

BESOTS SEBSORSHinds and wind shear in-situ sensors

B81-14563REHOtELI PILOTED VEHICLES

Aerial surveying of small areas from a smallremotely controlled drone

A81-17525Remotely piloted vehicles. Citations from the

International Aerospace abstracts data base[SASA-CB-163864] B81-14996

BESCDE OPEBATIOBSSarsat - A rescue system for ships and aircraft

A81-16684RESEARCH AIRCRAFT

Shipboard trials of the Quiet Short-Haul BesearchAircraft /QSBA/

A81-16581RBSEABCB ABO DBVELOPBEIT

The implications of current flight controlresearch and developnent

A81-16578RBSEABCH FACILITIES

Effects of downstream distance on turbulence decayfor the compressor research facility lowconditioning system[AD-A091543] B81-14276

Advanced flight deck/crew station simulatorfunctional requirements[BASA-CR-159331] N81-14994

BBSEABCB PROJECTSA summary of proposals for airflight research by

the BBFTA81-19298

RESOIAHT FREQUEHCIBSThe resonance frequencies of ventilated wind tunnels

[ABC-B/a-3841] B81-15009BEHOLDS BOHBBB

Hind-tnnnel measurements and comparison withflight of the boundary layer and heat transferon a hollow cylinder at Bach 3[BASA-TP-1789] B81-14975

RIGID ROTOR HELICOPTERSEngine-airfraae transient compatibility - Analysis

and testA81-17517

RIGID BOTORSRingeless tailrotor in fiber composite

construction and vibration-isolation systems/ABIS, ASIS/ for helicopters[SBB-DD-311-80-0] A81-19300

RIGID STBOCTOBESIntroduction to a rigid pavement design procedure

A81-18054BUS STRUCTURES

On the steady state and dynamic performancecharacteristics of floating ring bearings[ A S M E PAPER 80-C2AOB-17] A81-18671

A-29

BOBDSTBBSS (BATBEflATICS) SOBJECT IIOEX

EOBOSTHBSS (HATHBHATICS)Application of vector performance optimization to

a robust control loop design for a fighteraircraft[DFVLB-FB-80-1U] B81-13970

SOCKET EB6IIESA study of air breathing rockets - Subsonic oode

combustion[IAF PAPEB 80-F-270] A81-18371

BOLLThe effect of aerodynamic coupling on the dynamics

of aircraft in fast rolling motionA8 1-17 471

BOLLEH BEABUGSCalculated and experimental data for a 118-mm bore

roller bearing to 3 million DH[ASHE PAPBB 80-C2/IOB-11] A81-18668

Performance of computer-optimized tapered-rollerbearings to 2.4 million DN[ASHE PAPER 80-C2/LUB-18] 481-18672

Lubrication of rolling element bearingsA81-18738

BOIABT STABILITYAn experimental investigation of the rotating

stall/ surge, and wake behind the rotor for asingle stage axial compressor

481-17826Dynamic characteristics of a high-speed rotor with

radial and axial foil-bearing supports[ A S H E PAPER 80-C2/LOB-35] A81-18683

BOIABT ilHS AIECBAFTAircraft icing instrumentation: Unfilled needs

rotary wing aircraftH81-14S60

BOTABI 0IHGSPractical aerodynamics of the helicopter Hi-6A

Russian bookA81-18600

A loir height 2300 kf helicopter transmission withan enclosed planetary gear[ASHE PAPEB 80-C2/DET-17] A81-18642

Service life determination for the OH-60-A (UTTAS)helicopter elastomeric bearings[AD-A091756] H81-14324

A pure direct force/moment control for coaxialcounterrotating rotors

»81-15007BOTATING STALLS

An experimental investigation of the rotatingstall/ surge, and wake behind the rotor for asingle stage axial compressor

A81-17826BOTOB ABBODIBAHICS

An experimental investigation of the rotatingstall, surge, and wake behind the rotor for asingle stage axial compressor

A81-17826Practical aerodynamics of the helicopter Hi-6A

Russian bookA81-18600

Botor model for verification of computation methods[ISD-262] H81-15167

BOTOB BLADES (TOBBOHACHIiEBY)Structure and decay characteristics of turbulence

in the near- and far-vake of a moderately loadedcompressor rotor-blade[ASHE PAPEB 80-GT-95] 481-17954

Botor model for verification of computation methods[ISD-262] H81-15467

BOTORCRAFT AIRCRAFTTesting model rotorcraft for overvater operations

A81-18058BOTOBS

The effect of cyclic loading on the apparentcleavage fracture toughness of 1Cr-Ho-v rotorsteel

A81-17488Dynamic characteristics of a high-speed rotor with

radial and axial foil-bearing supports[ASBE PAPER 80-C2/UJB-35] A81-18683

Mechanisms of damage accumulation intime-dependent cyclic deformation[ DOE/EH-10570/1] H81-14363

Probabilistic analysis of foundation forces for aclass of unbalanced rotating machines

H81-15362BUBSAT COBDITIOBS

Runvay rehabilitation, Washington National AirportA81-18066

Fully bonded concrete overlay for an airport runwayA81-18075

BOHiATSFrestressed concrete airfield pavements

A81-18063OK pavement design and evaluation - A new approach

A81-18076Bunvay Configuration Hanagement System concepts

481-18089

SAFETY DEVICESPyrotechnics serving safety in aircraft air

and ground escape systemsA81-19348

SAFETY FACTOKSSafety considerations for helicopter drive systems

of the 1980sA81-17510

SAFETY HABAGEHEBTAn investigation of safety hazards and reliability

problems in aerial refueling stores[AD-A091788] H81-13938

Commuter airline safety[PB81-104267] H81-14988

SA8SATSarsat - A rescue system for ships and aircraft

A81-16684SATELLITE BA7IGATIOB SYSTBHS

Characteristics of N A V S T A B user stationsA81-19425

SATELLITE OBSEBVATIOBCatalog of sea state and wind speed in the South

Atlantic Bight[SASA-CB-156872] M81-14601

SADDI ABABIASaudi Arabia's new Gateway Airports

A81-18093SCALE HODELS

Rotary balance data for a single-engineagricultural airplane configuration for anangle-of-attack range of 8 deg to 90 deg[BASA-CB-3311] H81-13923

Active control of an explosive wing-store fluttercase[HBB-FE-17/S/POB/25] H81-13973

Effects of angle of attack and ventral fin ontransonic flutter characteristics of anarrow-wing configuration[BASA-TM-81914] N81-15397

SCHEDOLIBGPerformance evaluation of an interrogation-reply

scheduling technique for a discrete addressbeacon system of radar surveillance andaircraft communication in ATC

A81-19417SEA STATES

Catalog of sea state and wind speed in the SouthAtlantic Bight[BASA-CB-156872] B81-14601

SEALIBGSealing joints and cracks, thin resurfacing, and

locating voids under concrete slabs[PB80-215635] H81-14182

SEPARATED FLO!Experiaental investigation of a right angle wing

with partially separated flow with and withoutground effects[DGLH PAPEB 80-111] A81-19397

Experimental study of supersonic viscous leesideflow over a slender delta wing[BASA-TH-81248] B81-14265

An analytic model of subsonic flow around anairflow with a spoiler

M81-14966in investigation of support-interference effects

[BAL-TB-622] N81-14984SERVICE LIFE

Service life determination for the DH-60-A (UTTAS)helicopter elastomeric bearings[AD-A0917S6] B81-14324

SHAFTS {HACHUB ELEHBBTSIImproved capabilities to detect incipient bearing

failures[AD-A091687] B81-14325

A-30

SOBJECT IHDBI STE1DT FLO!

SBEAB LAYERSDialogue on bridging sone gaps in stability andtransition research in external, internaland free-shear layer through-flow systems

A81-18105The velocity induced by the vake of a wind turbine

in a shear layer, including ground effect[FFA-TN-HO-2189-PT-3] B81-14985

SBEAE STBESSBeviev of theoretical and experimental results on

three dimensional turbulent wakes and boundarylayers[OBEBA-BT-1980-4] 881-13930

SHIPSSarsat - A rescue system for ships and aircraft

A81-16684SHOCK TESTS

Development of high-temperature turbine subsystemtechnology to a technology readiness status,phase 2[FE-1806-72] B81-14332

SHOCK IAVE PBOPAGATIOBStationary displacement of a body by a shock wave

A81-17622Experimental investigations on shock-associatednoise

A81-17735Comparison of experimental and computational shockstructure in a transonic compressor rotor[ASBE PAPEB 80-GT-81] A81-17953

The sonic boom fron an aircraft flying along anarbitrary path in a stratified atmosphere in thepresence of a three-component wind

A81-19636SBOET HAUL lIBCBAPT

Shipboard trials of the Quiet Short-Haul BesearchAircraft /QSBA/

A81-16581SHOBT TAKEOFF AIBCB&FT

Shipboard trials of the Quiet Short-Haul BesearchAircraft /QSBA/

A81-16581A case study in aircraft design: The de Havilland

family of STOL commuter aircraft BookA81-16717

Turbopropeller engine PZL-10SA81-1732U

The introduction of STOL and BBAV to largecommercial operations

A81-18057SBBODDED PBOPELLEBS

Aerodynamic design of a ducted propeller -Optimization of efficiency

A81-171U6SIGHAL ABALYSIS

Detection of moving objects Bnssian bookA81-18773

SKII (STBDClOBAL HEBBEB)Application of fracture mechanics in designing

lower wing skin of transport aircraftA81-17049

SKIS FRICTIOBHind-tunnel measurements and comparison with

flight of the boundary layer and heat transferon a hollow cylinder at Bach 3[BASA-TP-1789] H81-1U975

SLEIDEB BIBGSThe determination of the induced drag on slim

wings with high lift systems in the transonicregion[HBB-FE122] A81-19400

Nonlinear aerodynamic characteristics of a thinairfoil of arbitrary plane configuration

A81-19629Thin minimum-drag airfoils

A81-19630SLOTTED WIBD TOHBELS

The resonance freguencies of ventilated wind tunnels[ABC-B/S-3841] B81-15009

SOLID PHASESFormation of solid phase during the heating of jet

fuelsA81-17372

SOLID STATE DEVICESSolid-state power system use expands

A81-19491

SOIIC BOOBSThe sonic boon from an aircraft flying along an

arbitrary path in a stratified atmosphere in thepresence of a three-component wind

A81-19636SOBIC HOZZLES

Effects of axisymmetric sonic nozzle geometry onHach disk characteristics

A81-18022SOOBD FIELDS

Experimental investigations on shock-associatednoise

A81-17735SOOBD PBESSDBE

Analysis of pressure spectra neasurements in aducted combustion system[ KASA-TM-81583] B81-15768

SODBD iAVESSound radiation from a finite length unflanged

circular duct with uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

&81-16712Periodically stiffened fluid-loaded plates. I -

Besponse to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067Propagation of three-dimensional acoustic

perturbations in channels of variablecross-sectional area at freguencies close tocutoff freguency

A81-19338Prediction of sound radiated from different

practical jet engine inlets[NASA-CB-163824] H81-14789

Improved methods for fan sound field determination[NASA-CB-165188] B81-15769

SPACECBAFT COBHDBICATIOHSatellites to aid flight safety

[IAF PAPEB 80-IAA-17] A81-18410SPACBCBAFT PBOPDLSIOB

A study of air breathing rockets - Subsonic modecombustion[IAF PAPEB 80-F-270] A81-18371

SPABK IGHITIOBAdvanced Technology Spark-Ignition Aircraft Piston

Engine Design study[BASA-CB-165162] H81-13963

SPIB TESTSA status report on BASA general aviation

stall/spin flight testingA81-19471

SPLIBESPrevention of spline wear by soft metallic coatings

aircraft engines[AD-A091861] N81-14064

SPOILEBSTheoretical investigation of the influence of

spoiler dynamics on the handling qualities of anaircraft with direct lift control[DFVLB-FB-80-07] B81-13975

An analytic model of subsonic flow around anairflow with a spoiler

B81-14966SPBAIBD COATIBGS

Coatings in the aero gas turbineA81-17167

STABILITY AUGHEUTATIOHEconomic evaluation of flying-qualities design

criteria for a transport configured with relaxedstatic stability[BASA-TP-1760] B81-13968

STATISTICAL ANALYSISStatistical relationship between median visibility

and conditions of worstcase lanmade impact onvisibility[LA-OB-80-2485] N81-14550

The annoyance caused by noise around airports[BASA-Ta-75784] B81-15579

STATISTICAL DBCISIOB TBEOBTRenewal function for any arbitrary period - A

Bayesian wayA81-16939

STEADI FLOISteady flow past a rectangular wing with

circulation that is variable along the spanA81-16551

A-31

STIFFBESS SDBJECT IHDBX

Finite difference computation of the steadytransonic potential flow around airplanes

A81-17802STIFFHBSS

The rigidity and performance of a simple spiralbevel helicopter gearbox[ A S H E PAPEB 80-C2/DET-103] A81-18654

STIFFHBSS HATBIIThe matrix analysis of wings

A81-17818STIBLIHG CICLE

Power control for hot gas engines[HASA-CASE-HPO-14220-1] N81-14318

STOCHASTIC PROCESSESFrequency-shaped cost functionals - Extension of

linear-quadratic-Gaassian design methodsA81-18578

STBESS ABALYSISStructural analysis of fuselages with cutouts by

finite element method481-17816

The stress behavior of three advanced nickel basesuperalloys during high temperature low cyclefatigue[AD-A091694] H81-14061

STUESS-STBAIH-TIHE RELATIO8SBechanisms of damage accumulation in

time-dependent cyclic deformation[DOE/EB-10570/1] H81-14363

STBUCTOBAL ANALYSISExperimental analysis and methods to determine the

dynamic behavior of propulsion shafting systemsH81-15401

STBOCTDBAL DESIGHIntroduction to a rigid pavement design procedure

A81-18054SNIAS helicopters

A81-19342A computer program for the design and analysis of

low-speed airfoils, supplement[NASA-TM-81862] N81-13921

Dual methods and approximation concepts instructural synthesis[NASA-CR-3226] H81-143U7

STBOCTDBAL DESIGH CBITEBIAAdvanced transmission component development and

test program for helicoptersA81-17507

Safety considerations for helicopter drive systemsof the 1980s

A81-17510Clear air turbulence: Historical comments

N81-14562STRUCTURAL RELIABILITY

Fully bonded concrete overlay for an airport runwayA81-18075

Becent developments in HDT techniques forairport pavement testing

A81-18078STBOCTOBAL STABILITY

On the steady state and dynamic performancecharacteristics of floating ring bearings[ASHE PAPEB 80-C2/LOB-17] A81-18671

STBOCTOBAL VIBBATIOHPeriodically stiffened fluid-loaded plates. I -

Besponse to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067On the steady state and dynamic performance

characteristics of floating ring bearings[ASHE PAPEB 80-C2/10B-17] A81-18671

Hodel vibrations beyond low-speed stallA81-19552

SOBCBITICAL FLOSAerodynamic calculations and design of subcritical

aerofoilsA81-17801

SOBSOSIC FLOBA study of air breathing rockets - Subsonic mode

combustion[ I A F PAPEB 80-F-270] A81-18371

Some characteristics of subsonic flow over theroot area of a sweptback wing

A81-19633Plane vortex gas flows emphasizing supersonic

caseA81-19631

Laser-Baman/Bayleigh flow diagnostic techniquesapplied to subsonic flow[AD-A091695] S81-11275

An analytic model of subsonic flow around anairflow with a spoiler

H81-14966Finite element analysis of inviscid subsonic

boattail flow[HASA-TH-81650] H81-14977

SOBSOHIC SPEEDCalculation of the lift dependent drag polar of

cambered fighter plane configurations withdeflected maneuver flaps in the subsonic regionby means of a modified procedure according toLanar[OGLE PAPEB 80-109] A81-19395

SUCTIONThin minimum-drag airfoils

A81-19630SUPERCRITICAL HIHGS

The supercritical profile of the supercritical wingA81-17522

SDPEBSOIIC AIBCBAFTOptimum selection of main parameters for the

reverse design of a supersonic military aircraftA81-17047

Transonic axisymmetric bodies with minimal wave dragA81-170U8

One-dimensional considerations concerning thestability behavior of inlet diffusers forsupersonic aircraft German thesis

A81-17548Sukhoi's pivotal interdictor

A81-17832Industry proposes supersonic V/STOL

A81-19490A system for aerodynamic design and analysis of

supersonic aircraft. Part 1: Generaldescription and theoretical development[HASA-CB-3351] N81-14970

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 3: Computer programdescription[HASA-CB-3353] N81-14971

SDPEBSOHIC BOUBDABI LAIEBSThe coordinate-deformation method in the problem

of a supersonic gas flow over an airfoildelta wings

A81-19631The influence of flow disturbances on the

laminar-turbulent transition in a supersonicboundary layer

A81-19643Hind-tunnel measurements and comparison with

flight of the boundary layer and heat transferon a hollow cylinder at Bach 3[BASA-TP-1789] N81-14975

SOPEBSOHIC CBOISE AIBCBAFT BESEABCBBibliography of Supersonic Cruise Besearch (SCB)

program from 1977 to mid-1980[NASA-BP-1063] H81-10973

SDPEBSOHIC DIFFDSEHSOne-dimensional considerations concerning the

stability behavior of inlet diffusers forsupersonic aircraft German thesis

A81-17548SOPKBSOHIC DBAG

Procedures for optimal drag design of camber andflap deflection in supersonic regions withconsideration to geometric limits[DGLB PAPEB 80-110] A81-19396

SDPEBSOSIC FLIGHTComputational aerodynamic design tools and

techniques used at fighter development[HBB-FE-122/S/PUB/13J K81-13950

SOPERSOHIC FLO!Characteristics of the velocity field near a

wing-body combination located at an angle ofattack to an oncoming supersonic flow

A81-19337Plane vortex gas flows emphasizing supersonic

caseA81-19634

Downwash calculation at close range behind atrapezoidal wing in supersonic flow[FFA-TH-AU-1661] H81-13925

A-32

SUBJECT IHDJSI TBHPBB1TOBE COHTBOL

SOPEBSOHIC FLDTTBBExperimental determination of ansteady blade

element aerodynamics in cascades. Volume 2:Translation mode cascade[NAS1-CH-165166 ] H81-1II976

SOPEBSOHIC IHLETSSupersonic stall flatter of high speed fans in

turbofan engines[SASA-TB-81613] B81-14978

SDPBBSOIIC 1IHD IOH8LSTbe influence of flow disturbances on the

laminar-turbulent transition in a supersonicboundary layer

A81-19613Rail cooling and the laminar-turbulent boundarylayer transition at supersonic flow velocities

A81-19644SUPPOBT IHTBBFBREHCE

An investigation of support-interference effects[NAL-TB-622] S81-14981

SOPPBESSOBSAdvanced technology turboshaft IB suppression

A81-17519General Electric infrared suppressors for the

Black Hawk helicopterA81-17520

SORFACE COOLIHGHall cooling and the laminar-turbulent boundary

layer transition at supersonic flow velocitiesA81-19614

SOBFACB DEFECTSBunway rehabilitation. Washington National Airport

A81-18066SDBFACE FIBISHIHG

Surface analysis of bearing steels after solventtreatments. II - Lubricant-coated bearing surfaces[ASLE PBEPBINT 80-LC-8A-6] A81-18748

Surface finishing[HASA-CASE-BSC-12631-3] 118 1-11077

SDBFACB BOOGHIESSA computer program for the design and analysis of

low-speed airfoils, supplement[8ASA-TB-81862] H81-13921

SDBSBSAn experimental investigation of the rotating

stall, surge, and wake behind the rotor for asingle stage axial compressor

A81-17826SOBVBILLAHCB BADAB

Performance evaluation of an interrogation-replyscheduling technique for a discrete addressbeacon system of radar surveillance andaircraft communication in ATC

A81-19417SOSPBMSIOB STSTBHS (VEHICLES)

Heave instabilities of amphibious air cushionsuspension systems[OTIAS-246] H81-15156

SIEPI BIHSSLaminar boundary layer on swept-back wings of

infinite span at an angle of attack481-17656

Three-dimensional boundary layer transition viathe mechanisms of 'attachment linecontamination1 and 'cross flow instability*

A81-18122Some characteristics of subsonic flow over the

root area of a sweptback wingA81-19633

The effects of warhead-induced damage on theaeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091671] 1181-13955

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] H81-14986

STBCBBOBOOS SATELLITESAeronautical-Maritime Engineering Satellite /AHES/

program of Japan[IAF PAPEB 80-D-171] A81-18318

S1STEH EFFECTIVENESSProductivity - The challenge of aircraft and

engine maintenanceA81-17015

Hind shear systems integration plan, VICOS (visualconfirmation) reliability analysis[PB80-218233] H81-13949

SISTBHS ESGIBEBEIH6The future ATC system as influenced by advanced

avionicsA81-16586

Bicrowave landing systems. Citations from theEngineering Index data base[PB80-814643] H81-13947

Bicrowave landing systems. Citations from theNils data base[PB80-814635] B81-139U8

SISTEBS IBTBGBATIOHAn overview - 1980 generation avionic developments

A81-18061SISTEHS HAHAGEBBHT

Airport/environs plan making - Banaging theplanning process

A81-18088STSIEBS SIHOLATIOS

Increasing capacity with computer-assisteddecision making airport planning

A81-18080Bodeling of the terminal area Air Traffic

Banagement and ControlA81-18085

Airspace simulation in airport system planningA81-18086

TABLES (DATA)Experimental aerodynamic characteristics of twoV/STOL fighter/attack aircraft configurations atBach numbers from 0.1 to 1.4[HASA-TB-81234] H81-14981

TAKEOFFHind shear systems integration plan, 7ICOH (visualconfirmation) reliability analysis[PB80-218233] N81-13949

TAKEOFF BOBSAirline flight departure procedures - Choosing

between noise abatement, minimum fuelconsumption and minimum cost

A81-17011TBCBIOLOGICAL FOBECASTIIG

An overview - 1980 generation avionic developmentsA81-18061

Aviation assumptions in the eightiesA81-18068

Avionics and displays in a future airspace systemA81-18070

Turbine blade technology - Present and future[ASHE PAPEB 80-C2/AEBO-10] A81-18639

Fighters for the 1990sA81-19497

TECHIOLOGI ASSESSBEBTThe implications of current flight controlresearch and development

A81-16578Head-Op-Display flight tests

A81-16582A cockpit view of advanced airline avionics

A81-16585Today and the future in aircraft wheel and brake

developmentA81-17016

fiolls-Boyce engines status reportA81-17166

TBCHBOLOSr TBABSFBBAn assessment of General Aviation utilization of

advanced avionics technology[HASA-CB-159328] N81-13911

TECHIOLOGI OTILIZATIOBThe future of civil turbo-fan engines

CPNB-90031] N81-13964TBLEVISIOS CABBBAS

Autonomous navigation using passively sensedterrain images

A81-17977Eguipment for testing and measuring a "helmet

mounted sight and display" system with a coupledmovable television camera in theflight-simulator for research of the DFVLH[DFVLB-BITT-80-04] B81-13960

TESPEBiTOEE COITBOLAdvanced technology tarboshaft IB suppression

A81-17519

A-33

TBHPERATORB EFFECTS SOBJECX IIDEI

TEBPBBATOBE EFFECTSFormation of solid phase during the heating of jet

fuelsA81-17372

TEBPEBITOBE SE1SOBSAn optimum design procedure of total-temperature

thermocouple probes&81-17807

TBRHINAL BALLISTICSThe effects of warhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] N81-13955

TBRHIHAL FACILITIESAirspace analysis in airport system planning

A81-18052Helicopters - Help for the all Heather terminal

A81-18065Investment decision-making in international airports

A81-18079Design of the new Tehran International Airport

A81-18084The importance of 'Interim Standard Hicrowave

Landing System1 for small community airportsA81-18087

Saudi Arabia's new Gateway AirportsA81-18093

TERSIHAL GUIDANCEFlight evaluation of the terminal guidance system

[NASA-CR-163859] H81-1M991Applicated techniques for the control of approach

traffic[DFVLB-BITT-79-20] H81-11992

TEBRAIN ABALISISAutonomous navigation using passively sensed

terrain imagesA81-17977

TBBBAIR FOLLOWING AIRCRAFTSukhoi's pivotal interdictor

A81-17832TEST EQOIPBBIT

Equipment for testing and measuring a "helmetmounted sight and display11 system with a coupledmovable television camera in theflight-simulator for research of the DFVLR[DFVLR-BITT-80-04] N81-13960

IF-31 ESCIHETF34 engine compression system computer study

simulation of flow stability[HASA-CB-159889] H81-15005

TBEBBAL COHTBOL COATIBGSCost/benefit analysis of advanced materials

technologies for future aircraft turbine engines[NASA-CR-165225] N81-15006

TBERHAL STABILITYJoint-laboratory qualification testing of oils for

gas turbine enginesA81-17375

TSEBBOCOOPLESAn optimum design procedure of total-temperature

thermocouple probes481-17807

TBEBHODTBAHIC PBOPEBTIESTime dependent Navier-Stokes solution of a

turbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

H81-14964TBERHOPLASTIC BESIHS

A resin injection technique for the fabrication ofaero engine composite components[PHR-90024] N81-14004

IBIS nsesDetermination of the effect of transverse cutouts

on the hydrodynamic characteristics of afinite-span wing in the case of steady andunsteady motion near a wall

A81-19335TBBEE DIHEHSIOSAL BODIDABI LAIEB

Three-dimensional boundary layer transition viathe mechanisms of 'attachment linecontamination* and 'cross flow instability1

A81-18122Review of theoretical and experimental results on

three dimensional turbulent wakes and boundarylayers[ONEBA-HT-1980-4] N81-13930

THBEB DIHEHSIOBAL FLOIThe coordinate-deformation aethod in the problem

of a supersonic gas flow over an airfoildelta wings

A81-19631Pull potential solution of transonic guasi-3-D

flow through a cascade using artificialcompressability[HASA-TB-81637] H81-14980

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] N81-14986

Vortex methods for two- and three-dimensional flowsimulations

H81-15313TBBDST BEARIBSS

Dynamic characteristics of a high-speed rotor withradial and axial foil-bearing supports[ASBE PAPEB 80-C2/LDB-35] A81-18683

TBDBDBBSTOBBSThe microbnrst: Common factor in recent aircraft

accidentsH81-14571

Doctor Fujita's microburst analysis at ChicagoN81-14572

Lightning. Citations from the InternationalAerospace abstracts data base[NASA-CB-163857] N81-15648

TILT BOTOB RESEARCH AIBCB1FT PBOGRAHThe XV-15 tilt rotor research aircraft

A81-16588TIBS DEPEHDEBCE

Time dependent Havier-stokes solution of aturbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

N81-14964TOPOLOGI

Component-adaptive grid embeddingN81-14697

TOBQDEHind-tunnel test of an articulated helicopter

rotor model with several tip shapesCHASA-TH-80080] H81-13918

TBACKIHG (POSITIOH)Simulator study of conventional general aviation

instrument displays in path-following tasks withemphasis on pilot-induced oscillations[NASA-IP-1776] ' N81-14997

TRAILING EDGESStructure and decay characteristics of turbulence

in the near- and far-wake of a moderately loadedcompressor rotor-blade[ASHE PAPEB 80-GT-95] A81-17954

Downwash calculation at close range behind atrapezoidal wing in supersonic flow[ FFA-TH-AU-1661] H81-13925

TRAILIHG-EDGB FLAPSThe determination of the induced drag on slim

wings with high lift systems in the transonicregion[MBB-FE122] A81-19400

THAIHIH6 AIRCRAFTPrimary training of military pilots - Changing

theories and new trainersA81-19498

TBAIBIBG DEVICESVisual systems at Lufthansa's simulator centre •

A81-19499TRAJECTORI OPTIHIZATIOU

Evaluation of a computer-generated perspectivetunnel display for flight path following[BASA-TP-1736] N81-13958

TBABSITIOI FLOiDialogue on bridging some gaps in stability and

transition research in external, internaland free-shear layer through-flow systems

A81-18105TRABSLATIOHAL BOTIOH

Experimental determination of unsteady bladeelement aerodynamics in cascades. Volume 2:Translation mode cascade[BASA-CB-165166] N81-14976

Probabilistic analysis of foundation forces for aclass of unbalanced rotating machines

H81-15362TBAISBISSIOBS (BACBIHE ELEBEBTS)

Advanced transmission component development andtest program for helicopters

A81-17507

A-3«

SUBJECT IHDEI TOBBOF1B EHGIIBS

Drive system development for the 1980'shelicopter transmissions

A81-17508Development of helicopter transmission componentsfor the 1980s

A81-17509Hater content of helicopter gear oils

[ASHE PAPER 80-C2/DET-12] A81-18610A low height 2300 kf helicopter transmission vith

an enclosed planetary gear[&SHE PAPER 80-C2/DET-17] A81-186IJ2

Approximation of gear transmission error bystandard gear errors[ASHE PAPER 80-C2/DET-71] A81-186U6

Experience vith advanced high performance gear steelfor CH-47

[ASHE PAPEB 80-C2/DET-77] A81-18618Gas turbine engines and transmissions for bus

demonstration programs[COO-<4867-07] H81-1U329

TBABSOfXC COHPBESSOBSComparison of experimental and computational shock

structure in a transonic compressor rotor[ASHE PAPEB 80-GT-81] A81-17953

TBABSOHIC FLIGHTTransonic axisymmetric bodies Kith minimal wave drag

A81-17048The determination of the induced drag on slim

wings vith high lift systems in the transonicregion[H8B-FE122] A81-19400

An evaluation of vind tunnel test techniques foraircraft nozzle afterbody testing at transonicHaeh numbers[AD-A091775] N81-13931

TBABSOHIC FLOBThe supercritical profile of the supercritical wing

A81-17522Finite difference computation of the steady

transonic potential flow around airplanesA81-17802

An aerodynamic design method for transonic axialflow compressor stage

A81-17805Component-adaptive grid embedding

H81-14697An investigation into grid patching techniques

B81-14708Transonic vind tunnel tests on an oscillating wing

vith external store. Part 4: The ving withunderving: Store[AD-A077370] H81-1<1969

Full potential solution of transonic quasi-3-Dflow through a cascade using artificialcompressability[NASA-TB-81637] B81-14980

A method for obtaining shockless transonic flowspast airfoils, partially modified from a givenarbitrary airfoil[B&L-TB-602T] B81-14983

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] B81-14986

TBAHSOHIC FLUTTEREffects of angle of attack and ventral fin on

transonic flutter characteristics of anarrow-wing configuration[HASA-TB-81914] H81-15397

TBABSOBIC BIBD TOiiELSFurther investigations of adaptive-wall wind tunnels

[AP-A09177U] N81-13977TBABSPOBT AIRCRAFT

Principle for the design of hybrid control systemsfor passenger transport systems

A81-17577Fundamentals of conceptual design optimization of

subsonic transport aircraft[VTH-LB-292] N81-13951

Laminar-airfoils for transport aircraft[DFVLB-HITT-80-07] H81-13952

Economic evaluation of flying-qualities designcriteria for a transport configured vith relaxedstatic stability[HASA-TP-1760] B81-13968

Theoretical investigation of the influence ofspoiler dynamics on the handling qualities of anaircraft vith direct lift control[DFVLH-FB-80-07] B81-13975

A survey of nev technology for cockpit applicationto 1990's transport aircraft simulators[HASA-CB-159330] B81-14993

Advanced flight deck/crew station simulatorfunctional requirements[NASA-CB-159331J B81-14994

TBAHSPOBTATIOB BBTBOBKSA new perspective in aviation systems planning

&81-18069TRAPEZOIDAL BIB6S

Dovnvash calculation at close range behind atrapezoidal wing in supersonic flow[FFA-TS-AU-1661] N81-13925

TOBBISE BLADESTariational principles and generalized variational

principles for the hybrid aerodynamic problem ofairfoil cascades on an arbitrary stream sheet ofrevolution

A81-17741Turbine blade technology - Present and future

[ASBE PAPEB 80-C2/AERO-10] A81-18639TDBBIME ESGIBBS

Helicopter propulsion system development andqualification

A81-17511TBBBISE iHEELS

Comparison of experimental and computational shockstructure in a transonic compressor rotor[ASBE PAPEB 80-GT-81] A81-17953

TOBBIHESSome aspects of optimizing the aerodynamics of

turbine stagesA81-19325

TDBBOCOHPBESSOBSAn aerodynamic design method for transonic axial

flow compressor stageA81-17805

A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-17824An experimental investigation of the rotating

stall, surge, and vake behind the rotor for asingle stage axial compressor

A81-17826Inlet flow distortion in turbomachinery

[ASBE PAPEB 80-GT-20] A81-17952Comparison of experimental and computational shock

structure in a transonic compressor rotor[ASHE PAPER 80-GT-81] A81-17953

Structure and decay characteristics of turbulencein the near- and far-wake of a moderately loadedcompressor rotor-blade[ASBE PAPER 80-GT-95] A81-17954

Supersonic stall flutter of high speed fans inturbofan engines[BASA-TB-81613] 881-14978

Aerodynamic stability analysis of NASAJ85-13/planar pressure pulse generatorinstallation[BASA-CR-1651U1] N81-15004

TF34 engine compression system computer studysimulation of flow stability[BASA-CB-159889] B81-15005

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15332/T1] B81-15414

TDBBOFA8 AIBCBAFTSukhoi's pivotal interdictor

A81-17832TOBBOFAH EHGIHES

Bolls-Royce engines status reportA81-17166

The future of civil turbo-fan engines[PSfl-9003!»] N81-13961

Supersonic stall flutter of high speed fans inturbofan engines[BASA-TB-81613] H81-1U978

Flight evaluation of a simplified gross thrustcalculation technique using an F100 turbofanengine in an F-15 airplane[BASA-TP-1782] H81-15000

Application of the BBA design method to anonlinear tnrbofan engine multivariableByquist array method[BASA-CB-163855] H81-15001

Improved methods for fan sound field determination[HASA-CB-165188] N81-15769

A-35

IORBOFAHS SUBJECT IHDSI

TUBBOFANSTF34 engine compression system computer study

simulation of flow stability[NASA-CB-159889] N81-15005

TOBBOJBT EH6IHB COBTBOLApplication of the UNA design method to a

nonlinear turbofan engine multivariableHyguist array method[HASA-CB-163855] B81-15001

TDEBOJBT EBGIBBSBolls-Boyce engines status report

181-17166A preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

A81-17824The measurement and analysis of station parameters

of a turbojet engine481-17825

Conditions of generation and methods of dampingthe inlet vortex of a turbojet engine

481-19442TDBBOHACBIHB BLADES

Supersonic stall flutter of high speed fans inturbofan engines[NASA-TM-81613] H81-14978

Solution of plane cascade flow using improvedsurface singularity methods application ofpanel method to internal aerodynamics[NASA-TH-81589] N81-14979

Full potential solution of transonic guasi-3-Dflow through a cascade using artificialcompressability[NASA-TH-81637] N81-14980

Aerodynamic stability analysis of NASAj85-13/planar pressure pulse generatorinstallation[NASA-CB-165111] N81-15004

TOBBOPBOP BBGIBESTurbopropeller engine PZL-10S

A81-17324lOBBOSBAFTS

The impact of contingency ratings on advancedturboshaft engine design

A81-17502Issues regarding Army tnrboshaft enginesdiagnostics and condition monitoring

AS 1-17 514TURBULENCE

Time dependent Navier-Stokes solution of aturbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

N81-1496MTOEBOLEST BOOHDABY LATEB

Influence of free-stream turbulence intensity onheat transfer in the two-dimensional turbulentboundary layer of an accelerated compressible flow

A81-17994The influence of flow disturbances on the

laminar-turbulent transition in a supersonicboundary layer

A81-19643Beview of theoretical and experimental results on

three dimensional turbulent wakes and boundarylayers[ONEBA-NT-1980-4] N81-13930

TUEBULEHT PLOWDialogue on bridging some gaps in stability and

transition research in external, internaland free-shear layer through-flow systems

A81-18105Plane vortex gas flows emphasizing supersonic

caseA81-19634

Effects of downstream distance on turbulence decayfor the compressor research facility lowconditioning system[AD-A091543] N81-14276

Time dependent Navier-Stokes solution of aturbulent gas jet ejected f r o m a rectangularorifice into a high-subsonic crossflow

N81-14964TUBBULEHT BEAT TBANSPEB

Influence of free-stream turbulence intensity onheat transfer in the two-dimensional turbulentboundary layer of an accelerated compressible flow

A81-17994

TOBBOLEHT JETSApplication of optical methods to the study of jet

noise and turbulence[ISL-CO-201/80] B81-15819

TOBBOLB8T RAKESAn experimental investigation of the rotating

stall, surge, and wake behind the rotor for asingle stage axial compressor

A81-17826Structure and decay characteristics of turbulence

in the near- and far-wake of a moderately loadedcompressor rotor-blade[ A S H E PAPEB 80-GT-95] A81-17954

Beview of theoretical and experimental results onthree dimensional turbulent wakes and boundarylayers[OHEBA-NT-1980-4] H81-13930

The velocity induced by the wake of a wind turbinein a shear layer, including ground effect[FFA-TH-HD-2189-PT-3] B81-14985

TIO DIMENSIONAL BODBDABY LATEBInfluence of free-stream turbulence intensity on

heat transfer in the two-dimensional turbulentboundary layer of an accelerated compressible flow

A81-17994TIO DIHEISIONAL FLOB

Plane vortex gas flows emphasizing supersoniccase

A81-19634An analytic model of subsonic flow around an

airflow with a spoilerB81-14966

uOB-601 HBLICOPTBfi

General Electric infrared suppressors for theBlack Hawk helicopter

A81-17520DBIFOBB PLOB

Sound radiation f rom a finite length unflangedcircular duct with uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712UBBAH PLABBIBG

Community participation in airport planningA81-18067

DBBAB TBABSPOBTATIOSA new perspective in aviation systems planning

A81-18069Gas turbine engines and transmissions for bus

demonstration programs[COO-4867-07] N81-14329

OSEB SANDALS (COHPUTEB PBOGBiHS)A system for aerodynamic design and analysis of

supersonic aircraft. Part 2: User's manual[NASA-CB-3352] N81-13920

DSEB BEQOIBBBEHTSBNAV benefits today - Today and future requirements

A81-18056

V/STOL AIBCBAFTIndustry proposes supersonic V/STOL

A81-19490Experimental aerodynamic characteristics of two

V/STOL fighter/attack aircraft configurations atHach numbers from 0.4 to 1.4[NASA-TB-81234] N81-14981

VALUE EHGIBEEBIN6Aircraft engine programs employing cost objectives

A81-19346VABADIDH COHPOOBDS

Vanadium trineodecanoate promoter forfiberglass-polyester soil snrfacings[AD-A091785] H81-14084

VAPOUZIBGA vaporizing combustor with double combustion spaces

A81-17827VARIABLE SHEEP BIBGS

Sukhoi's pivotal interdictorA81-17832

4-36

SUBJECT ISDBI •HO (HBTBOBOLOGI)

TABIATIORAL PBINCIPLESVariational principles and generalized variational

principles foe the hybrid aerodynamic problem ofairfoil cascades on an arbitrary strean sheet ofrevolution

A81-17741VECTOR ANALYSIS

Application of vector performance optimization toa robust control loop design for a fighteraircraft[DFVLB-FB-80-14] H81-13970

VELOCITY DISTBIBOTIOSCharacteristics of the velocity field near a

King-body combination located at an angle ofattack to an oncoming supersonic flow

A81- 19337VENTILATION PASS

Boise and noise abatement in fans and blowers: Areview[DFVLB-FB-80-16] N81-14796

VBBTICAL AIB CUBBBITSExperimental investigation of orographic waves and

vertical motions in the Krasnovodsk airport areaA81-19441

VIBBATION DAHPINGElimination of vibrations in aircraft piping systems

Russian boo*A81-18497

Passive control of wing/store flutter[HASA-TH-81865] N81-13922

TIBBATI01 EFFECfSBeview of engine/airframe/drive train dynamic

interface development problemsA81-17516

Engine-airframe transient compatibility - Analysisand test

A81-17517VIBBATION ISOLATOBS

Hingeless tailrotor in fiber compositeconstruction and vibration-isolation systems/ABIS, ASIS/ for helicopters[MBB-OD-311-80-0] A81-19300

VIBBATI01 TESTSBecent developments in HOT techniques for

airport pavement testingA81-18078

Nondestructive dynamic testingA81-19657

VISCOSITYTime dependent Navier-Stokes solution of a

turbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

N81-14964VISIBILITY

Statistical relationship between median visibilityand conditions of worstcase maamade impact onvisibility[LA-OB-80-2485] N81-14550

VISUAL AIDSVisual systems at Lufthansa's simulator centre

A81-19U99VISDAl FLIGHT

Airport visual approach, guidance and landingsystems - Airline pilots viewpoint

A81-18083Nidair and near midair collisions on two- andthree-dimensional curvilinear flight paths[DFVLB-FB-80-13] N81-13944

VISUAL PBBCBPTIOBA new system for the study of visual informationpresentation in aeronautics - GIBI

A81-16688VOLTAGE COBVEBTEBS (DC TO DC)

DC-to-DC power supply for light aircraft flighttesting[BASA-CB-163850] N81-14989

VOBTBI 4VOIDASCEConditions of generation and methods of damping

the inlet vorter of a turbojet engineA81-19442

VOHTEI SHEETSNonlinear aerodynamic characteristics of a thinairfoil of arbitrary plane configuration

A81-19629VOBTICK5

Plane vortex gas flows emphasizing supersoniccase

A81-19634

Experimental study of supersonic viscous leesideflow over a slender delta wing[SASA-TH-81248] N81-14265

Vortex methods for two- and three-dimensional flowsimulations

B81-15313

w•AKES

The practical application of the Rake BlockingCorrections according to Baskell for largewind tunnel models[DGLB PAPEB 80-112] A81-19398

BALL FLOIA wall interference analysis in wind tunnels

A81-17472The practical application of the Bake Blocking

Corrections according to Haskell for largewind tunnel models[DGLB PAPEB 80-112] A81-19398

1ABIISG SISTEHSHelicopter alarms - The use of ALAT incident and

accident record cardsA81-16689

•1BPA6BP-111 windscreen machining

[1-2232] 881-14995WATBB LAHDISG

Helicopter survivability in overwater situationsA81-18081

IATBB IAVESCatalog of sea state and vind speed in the South

Atlantic Bight[NASA-CB-156872] N81-14601

WAVE DIFPHACTIOSExhaust noise in flight: The role of acoustic

installation effects[PNB-90029] N81-14793

•ATE DBAGTransonic axisymmetric bodies with minimal wave drag

A81-17048•ATE PBOPAGATION

Becent developments in HOT techniques forairport pavement testing

A81-180788BAPON SISTEBS

Advanced Attack Helicopter /YAH-64/ - status reportA81-16580

•BABImproved capabilities to detect incipient bearing

failures[AD-A091687] N81-14325

•BAB INHIBITORSPrevention of spline wear by soft metallic coatings

aircraft engines[AD-A091861] N81-14064

•BAB TESTSThe wear of PTFE-containinq dry bearing liners

contaminated by fluids[ASLE PBEPBINT 80-LC-6B-3] A81-18758

Ferrography as a health monitor and a design aidfor the development of helicopter gearboxes

A81-18759Prevention of spline wear by soft metallic coatings

aircraft engines[AD-A091861] 1181-14064

REATBEBHeasuring weather for aviation safety in the 1980's

N81-14568IBATBBB FORECASTING

Federal Aviation Administration and Nationalleather Service Aviation Besearch and Development

N81-14558•BATHBB STATIOBS

Federal Aviation Administration and NationalHeather Service Aviation Besearch and Development

N81-14558WEIGHT (BASS)

Current aircraft survey (approach speeds, grossweights, and Dimensions)[PB80-225691] N81-13956

HID (HBTEOBOLOSI)Experimental investigation of orographic waves and

vertical motions in the Krasnovodsk airport areaA81-19441

iinds and wind shear in-situ sensorsN81-14563

A-37

BIHD DIBECTIOH SUBJECT IIDEI

BIHD DIEECTIOBLou-speed Hind-tunnel tests of two weathercocking

sensors[WSBL-0171-TSJ H81-1457S

•IHD EFFECTSThe sonic boom from an aircraft flying along an

arbitrary path in a stratified atmosphere in thepresence of a three-cooponent wind

A81-19636BUD SHEAR

Hinds and wind shear in-situ sensorsH81-14563

The oicroburst: Common factor in recent aircraftaccidents

H81-14571Doctor Fujita's microborst analysis at Chicago

H81-14572Clean air turbulence. Citations from the

International Aerospace Abstracts data base[HASA-CB-163863] H81-15649

BIHD TDDBEL APPARATUSA vaporizing coobustor with double combustion spaces

A81-17827BIHD TDHHEL HODELS

The practical application of the Hake BlockingCorrections according to naskell for largewind tunnel models[DGLR PAPER 80-112] A81-19398

Hodel vibrations beyond low-speed stallA81-19552

BIHD TDHHEL STABILITY TESTSLow-speed wind-tunnel tests of two weathercocking

sensors[BSRL-0171-TM] N81-14575

BIHD TOHHEL TESTSHodel vibrations beyond low-speed stall

A81-19552Some characteristics of subsonic flow over the

root area of a sweptback wingA81-19633

Hind-tunnel test of an articulated helicopterrotor model with several tip shapes[HASA-TM-80080] H81-13918

Passive control of wing/store flutter[HASA-TM-81865] N81-13922

Botary balance data for a single-engineagricultural airplane configuration for anangle-of-attack range of 8 deg to 90 deg[NASA-CB-3311] H81-13923

An evaluation of wind tunnel test technigues foraircraft nozzle afterbody testing at transonicflach numbers[AD-A091775] H81-13931

Evaluation of wind tunnel nozzle afterbody testtechniques utilizing a modern twin enginefighter geometry at Hach numbers from 0.6 to 1.2

IF-17 aircraft[AD-A091545] N81-13932

Advanced ejection seat for high dynamic pressureescape. Rind tunnel test[AD-A091810] H81-13940

Active control of an explosive wing-store fluttercase[HBB-FE-17/S/POB/25] H81-13973

Laser-Raman/Bayleigh flow diagnostic techniquesapplied to subsonic flow[AD-A091695] H81-14275

Transonic wind tunnel tests on an oscillating wingwith external store. Part 4: The wing withunderwing: store[AD-A077370] H81-14969

Hind-tunnel measurements and comparison withflight of the boundary layer and heat transferon a hollow cylinder at Hach 3[HASA-TP-1789] H81-14975

Experimental aerodynamic characteristics of twoV/STOL fighter/attack aircraft configurations atBach numbers f rom 0.4 to 1.4[HASA-TS-81234] H81-14981

An investigation of support-interference effects[HAL-TB-622] H81-14984

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] U81-14986

BIHD TOHHEL BALLSA wall interference analysis in wind tunnels

A81-17472

The practical application of the Bake BlockingCorrections according to Haskell for largewind tunnel modelsCDGLE PAPEH 80-112] A81-19398

Further investigations of adaptive-wall wind tunnels[AD-A091774] H81-13977

The resonance frequencies of ventilated wind tunnels[ARC-B/S-3841] H81-15009

BIRD IOHHELSA computer-based laser Doppler velocimeter

[DFVLB-HITT-79-14] H81-14289II ID TELOCIir

Catalog of sea state and wind speed in the SouthAtlantic Bight[HASA-CH-156872] H81-14601

BIHDHILLS (BIHDPOBKBED BACHIIES)Botor model for verification of computation methods

[ISD-262] H81-15467BIIDPOBBB OTILIZATIOH

Botor model for verification of computation methods[ISD-262] H81-15467

IIIDSHIELDSP-111 windscreen machining

[T-2232] H81-14995HUG LOADIHG

Circulation Control ding /CCW/ flight testsA81-19469

Effects of nonlinearities on wing store flutter[HBB-FE-17/S/POB/27] H81-13974

Transonic wind tunnel tests on an oscillating wingwith external store. Part 4: The wing withunderwing: Store[AD-A077370] H81-14969

BUG OSCILLATIOHSThe method of superelements in the dynamics of

complex structuresA81-16969

BUS PLAHFOBHSHonlinear aerodynamic characteristics of a thin

airfoil of arbitrary plane configurationA81-19629

Thin minimum-drag airfoilsA81-19630

Laminar-airfoils for transport aircraft[DFVLE-BITT-80-07] H81-13952

BUG PROFILESThe supercritical profile of the supercritical wing

A81-17522Stationary displacement of a body by a shock wave

A81-17622The matrix analysis of wings

A81-17818Some characteristics of subsonic flow over the

root area of a sweptback wingA81-19633

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] H81-14986

BIBS BOOTSSome characteristics of subsonic flow over theroot area of a sweptback wing

A81-19633BUG SLOTS

Determination of the effect of transverse cutoutson the hydrodynamic characteristics of afinite-span wing in the case of steady andunsteady motion near a wall

A81-19335BIHG SPAH

Steady flow past a rectangular wing withcirculation that is variable along the span

A81-16551HIHGS

Application of fracture mechanics in designinglower wing skin of transport aircraft

A81-170H9BOBKLOADS (PSICHOPBISIOLOGT)

BHAY benefits today - Today and future requirementsA81-18056

IV-15 AIBCBAFTThe XV-15 tilt rotor research aircraft

A81-16588

A-38

PERSONAL AUTHOR INDEXAERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 134) APRIL 1981

Typical Personal Author Index Listing

PERSONAL AUTHOR

COIE. 6. 1. II Simulating stud; of the interaction between the

propulsion and flight control systems of asubsonic lift fan VIOL[HASA-Ig-81239] H81-110*3

TITLE

1

REPORTNUMBER

NASAACCESSION

NUMBER

Listings in this index are arranged a'lphabetically by personal author. The titleof the document provides the user with a brief description of the subject matter.The report number helps to indicate the type of document cited (e.g.. NASAreport, translation. NASA contractor report}. The accession number is locatedbeneath and to the right of the title, e.g. N81-11043. Under any one author'sname the accession numbers are arranged in sequence with the IAA accessionnumbers appearing first.

ADABCZTK, J.Full potential solution of transonic quasi-3-D

flow through a cascade using artificialcompressability[UASA-TH-81637] N81-14980

ADABCZIK, J. J.Inlet f low distortion in turbomachinery

[ASBE PAPER 80-GT-20] A81-17952Supersonic stall flutter of high speed fans

[HASA-TB-81613] 1181-14978ADA8S, J. J.

Simulator study of conventional general aviationinstrument displays in path-following tasks withemphasis on pilot-induced oscillations[HASA-TP-1776] H81-14997

ADDI, A. L.Effects of axisymmetric sonic nozzle geometry on

Bach disk characteristicsA81-18022

ADICOFF, A.Vanadium trineodecanoate promoter for

fiberglass-polyester soil surfacings[AD-A091785] H81-14084

AICBEB, I.Rotor model for verification of computation methods

[ISD-262] N81-154674LBK, F.

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] N81-14300

ALCOBTA, J. A.Improved capabilities to detect incipient bearing

failures[AD-A091687] N81-14325

ALEKSEEV, H. A.Hall cooling and the laminar-turbulent boundary

layer transition at supersonic flow velocitiesA81-19644

ALLEi, B. E.Turbine blade technology - Present and future

[ASBE PAPER 80-C2/AEBO-10] A81-18639ALRAHG. J. B.

Engine-airframe transient compatibility - Analysisand test

A81-17517AHDEBSOI, I. J.

Dynamic characteristics of a high-speed rotor vithradial and azial foil-bearing supports[ASBE PAPER 80-C2/LOB-35] A81-18683

A8TIS. G. I.Airspace analysis in airport system planning

A81-18052ABAI, B.

An experimental study on kerosene-hydrogen hybridcombustion in a gas turbine combustor

A81-17841ABBHDTS, F. J.

Constant-amplitude and flight-by-flight tests onCEBP specimens(SBB-FE-2/S/POB-26] N81-14006

ABGIBT.S, J. B.Rotor model for verification of computation methods[ISD-262] 881-15467

ABBAOD, J. L.Controls of aeronautical structures under fatigue

testing by holographic pulsed lasersinterferometry[ISL-CO-218/79] N81-14300

ABTABOHOV, L. I.Practical aerodynamics of the helicopter Bi-6A

A81-18600ASTAFBV, 7. A.

Formation of solid phase during the heating of jetfuels

A81-17372ATTA, E. B.

Component-adaptive grid embeddingH81-14697

ATTEID6E. A. G.Is the engine helicopter-worthy

A81-17518AOPOII, B.

Review of theoretical and experimental results onthree dimensional turbulent wakes and boundarylayers[ONERA-NT-1980-4] N81-13930

B

881-15003

BACHALO, i. D.Fuel injector characterization studies[HASA-CH-165200]

BAILEI, B.Landing flying qualities evaluation criteria for

augmented aircraft[HASA-CB-163097] N81-13969

BAIBO, G. 1.Recent developments in NOT techniques

A81-18078BAKDT, P. A.

Detection of moving objectsA81-18773

BABCHE. J.A wall interference analysis

A81-17472BARESBBBG, B. J.

Fully bonded concrete overlay for an airport runwayA81-18075

BABKEB, B. B.Introduction to a rigid pavement design procedure

A81-18054BAB1ETT, B. E.

Surface analysis of bearing steels after solventtreatments. II - Lubricant-coated bearing surfaces[ASLE PREPRINT 80-LC-8A-6] A81-18748

BAROi. A.Aerodynamic design of a ducted propeller -Optimization of efficiency

A81-17146BATTLES. B. A.

Development of helicopter transmission componentsfor the 1980s

A81-17509

B-1

BiOEB, K. PBBSOIAL AOIHOB ISDEI

BAUBB. S.InflaeDce of free-stream turbulence intensity on

heat transfer in the two-dimensional turbulentboundary layer of an accelerated compressible flow

A81-1799UBBiTII, A. J.

Micro-wave landing system - An operational pointof view

A81-18055BBISHAKBB, P. B.

Investment decision-Baking in international airportsA81-18079

BBLOTSEBKOVSKII. S. B.Nonlinear aerodynamic characteristics of a thin

airfoil of arbitrary plane configurationA81-19629

BBHBAB. P. E.Productivity - The challenge of aircraft and

engine maintenanceA81-17045

BEHTLBI. L. B.The measurement of aero gas turbine noise

[PSB-90032] N81-14795BBB6BBOH, B. P.

Development of a computer program data base of anavigation aid environment for simulated IFBflight and landing studies[UASA-TH-8006II ] H81-13959

BEBHSTBIH. B. L.The stress behavior of three advanced nickel base

superalloys during high temperature low cyclefatigue[AD-A091694] N81-11061

BEBBIEB, B. L.Investigation of convergent-divergent nozzles

applicable to reduced-power supersonic cruiseaircraft[HASA-TP-1766] H81-14972

BEBBI. B. F.The rating of helicopter noise: Development of a

proposed impulse correction[NPL-AC-93] S81-1U792

BEBBI, J. 0.Hind-tunnel test of an articulated helicopter

rotor model with several tip shapes[NASA-TH-80080] H81-13918

BEBDBE, B. A.B N A V benefits today - Today and future reguirements

A81-18056BHAITACBABIA, D. 0.

Beneval function for any arbitrary period - ABayesian vay

A81-16939'BIEBTDEHPEL. E.

Equipment for testing and measuring a "helmetmounted sight and display'1 system vith a coupledmovable television camera in theflight-simulator for research of the DFVLBtDFVLB-HITT-80-04] H81-13960

BIHDEB. S.Experience vith advanced high performance gear steel

[ASHE P A P E B 80-C2/DET-77] A81-18648BIPPES. B.

Experimental investigation of a right angle wingwith partially separated flow with and withoutground effects[DELS PAPEB 80-111] A81-19397

BLAIDOB, C. J.The introduction of STOL and B H A V to large

commercial operationsA81-18057

BOCK, S.-B.Drag reduction through formation flight

[DGLB PAPEB 80-106] A81-19393BOEHIG, F. B.

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15*25/11 ] H81-11327

BOIKO, L. V.Composition of sludge formed in B-3T oil

A81-17373BOICB, L.

Probabilistic analysis of fonndation forces for aclass of unbalanced rotating machines

B81-15362BOILS, D.

The flying hologram - Latest in head-up displaysystems

A81-19500

BBAHHAH. B. B.The wear of PTFE-containing dry bearing liners

contaminated by fluidsC A S L E PBEPBIHT 80-LC-6B-3] A81-18758

BBISKS. I. B.F/A-18 full scale development test

A81-16579BBITTLE, C.

Airspace analysis in airport system planningA81-18052

BBOOKS, 1.The impact of contingency ratings on advanced

turboshaft engine designA81-17502

The T700 booster engineA81-17506

BBOIB. D. P.Low-speed wind-tunnel tests of two weathercocking

sensors[BSBL-0171-TS] H81-11575

BBOIB, B. J.F-111 windscreen machining

[1-2232] N81-10995BBOBBB, 6.

SNIAS helicoptersA81-19312

BBIKIHA, I. G.Laminar boundary layer on swept-back wings of

infinite span at an angle of attackA81-17656

BOCCI, B.Performance evaluation of an interrogation-reply

scheduling technique for a discrete addressbeacon system

A81-19<417BODD, L. D.

An investigation of safety hazards and reliabilityproblems in aerial refueling stores[AD-A091788] N81-13938

BOLL, J. 0.Advanced ejection seat for high dynamic pressure

escape. Bind tunnel test[AD-A091810] H81-13910

BOBCBAB, F. B.. JB.Flight evaluation of a simplified gross thrust

calculation technique using an F100 turbofanengine in an F-15 airplane[HASA-TP-1782] H81-15000

BOBEE?A, B. B.Joint-laboratory qualification testing of oils for

gas turbine enginesA81-17375

BOBKE, J. D.The Gossamer Condor and Albatross: A case study in

aircraft design[AV-B-80/5<10] A81-16721

BOBBOBS, L. T.A survey of propulsion systems'

malfunctions/failures resulting in helicoptermishaps

A81-17513BOIBAOB, 0.

Stress measurements on landing gear for the AirbusA-300 B2

A81-19299

CAI, I.The matrix analysis of wings •

A81-17818CAIHE, 0. A.

Digital control for helicopter powerplantsA81-17504

CABP, D. B.Proceedings: Fourth Annual workshop onaeteorological and Environmental Inputs toAviation systems[HASA-CP-2139] H81-1U555

Survey of Borkshops on aeteorological andEnvironmental Inputs to Aviation Systems

H81-1«556CAHPBELL, B.

Saudi Arabia's new Gateway AirportsA81-18093

CABACEBA, F.The microbnrst: Common factor in recent aircraft

accidentsH81-11571

B-2

PEBSOJA1 ADTBOB IHDBZ DIIII, C. S.

CAB8, B. P.An investigation into grid patching techniques

H81-14708CAUGHBY, 0. A.

Development of finite-volume methods forthree-dimensional transonic flows[SD-A090829] N81-14986

CASIBB. F. »., JB.Passive control of wing/store flatter

[HASA-TH-81865] H81-13922

CHAI, I. I.Transonic axisymmetric bodies with minimal Have drag

A81-170118CBAI6. J. 8.

The effects of warhead-induced damage on theaeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] N81-13955

CBBH. F.A preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

A81-17824CHESTi, L.

Effects of nonlinearities on wing store flutter[HBB-FE-17/S/POB/27] N81-13974

CBIHA, B. T.Finite element analysis of inviscid subsonic

boattail flow[HASA-TH-81650] N81-14977

CaiBZEI. H.A study of air breathing rockets - Subsonic mode

combustion[IAF PAPER 80-F-270] A81-18371

ceo, j.Botary balance data for a single-engine

agricultural airplane configuration for anangle-of-attack range of 8 deg to 90 deg[HASA-CR-3311] N81-13923

CBDHG, K.Aerodynamic stability analysis of NASA

J85-13/planar pressure pulse generatorinstallation[HASA-CB-165111] N81-15004

CBBALCSIK, I.The PZL-Sokol - Hew Polish helicopter

A81-17325CICOB, D. B.

Improved methods for fan sound field determination[N4SA-CR-165188] N81-15769

CLABI. J. B.Validation Methods Research for Fault-Tolerant

Avionics and Control Systems Sub-iorking Groupfleeting. CARE 3 peer review[BASA-CP-2167] N81-15702

COB, B. B.Calculated and experimental data for a 118-mm bore

roller bearing to 3 million DB[ A S H E PAPER 80-C2/LOB-14] A81-18668

COB, f. I., JB.Leading-edge deflection optimization for a highly

swept arrow wing configuration[8ASA-TP-1777] N81-14974

COLEHAS. R. 6.A system for aerodynamic design and analysis of

supersonic aircraft. Part 2: User's manual[HASA-CR-3352] N81-13920

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 3: Computer programdescription[HASA-CR-3353] B81-14971

COHG, 8.The measurement and analysis of station parameters

of a turbojet engineA81-17825

COHKLB, J. P.Organic compounds in the exhaust of a J8S-5

turbine engine[AD-A091712] H81-13966

COHBOLLI, 3. «.Federal Aviation Administration and National

Heather Service Aviation Research and DevelopmentN81-14558

COOK, J. P.Sealing joints and cracks, thin resurfacing, and

locating voids under concrete slabs[PB80-215635] N81-14182

COPLIH. J. F.The future of civil turbo-fan engines[PBH-90034] 881-13961

COPPI, CB.The Grumman Aerospace and Gnlfstream AmericanGulfstream III case study in aircraft design

A81-16720CORBIB, 3. C., JR.

* Observing lightning from ground-based and airbornestations

N81-14566COBDIB, F.

Design to cost and new technologiesA81-19347

COOHTSEI, S. J..Ferrography as a health monitor and a design aid

for the development of helicopter gearboxesA81-18759

COOSIBIX, J.Review of theoretical and experimental results onthree dimensional turbulent wakes and boundarylayersCOHERA-NT-1980-4] B81-13930

CBAGO. I. A.Testing model rotorcraft for overwater operations

A81-18058CBORBLL, B. T.

System for refurbishing and processing parachutes[NASA-CASE-KSC-11012-1] N81-14967

DAI, G.Experimental investigations on shock-associated

noiseA81-17735

DALE, J. H.Advanced technology turboshaft IB suppression

A81-17519DALLESAGHB, 6.

The resistance of tank protective measures tomicroorganisms[SNIAS-801-551-107] N81-1S072

DALI, K. C.System considerations in the implementation of

digital control[AAS 80-032] A81-19375

DA06BTBRT, D. C.Further investigations of adaptive-wall wind tunnels

[AD-A091774] N81-13977DAVID, G.

Characteristics of NAVSTAB user stationsA81-19425

DAI, D. L.Compressor configuration and design optimization

for the high reliability gas turbine[ DOE/ET-15425/T1] N81-14327

DE POIfB, S.Aerodynamic design of a ducted propeller -

Optimization of efficiencyA81-17146

DBAB, B. G.Increasing capacity with computer-assisteddecision making

A81-18080DECELLES. J. L.

Flight instrumentation requirements forall-weather approach and landing

A81-18059DBFBBBARI, G.

Effects of nonlinearities on wing store flutter[SBB-FE-17/S/PUB/27] B81-13974

DEBAITIO, J. B.Hind shear systems integration plan, VICOH (visualconfirmation) reliability analysis[PB80-218233] N81-13949

DIEBKB. B.Equipment for testing and measuring a "helmet

mounted sight and display" system with a coupledmovable television camera in theflight-simulator for research of the DFVLR[DFVIB-HITT-80-04] N81-13960

DIXIT, C. S.Optimum selection of main parameters for thereverse design of a supersonic military aircraft

A81-17047

B-3

DOGGBTT, B. V. PEBSOIAL AUTHOR IIDKI

DOGGETT, B. V.Effects of angle of attack aod ventral fin on

transonic flutter characteristics of anarrow-wing configuration[NASA-TK-81914] H81-15397

DOHG. Q.The measurement and analysis of station parametersof a turbojet engine

481-17825DOBOFF, S. B.

Dynamic characteristics of a high-speed rotor withradial and axial foil-bearing supports[ASHE P&PEB 80-C2/10B-35] A81-18683

DOTLB, B. B.Airport/environs plan making - nanaging the

planning processA81-18088

DRAAH. A. H.Transonic wind tunnel tests on an oscillating wing

vith external store. Part 4: The ving withunderving: store[AD-A077370] H81-14969

DBAGO, 7. J.Hen major O.s. airports - Capacity considerations

481-18060DROSTE, C. S.

4 case study on the F-16 fly-by-wire flightcontrol system

A81-16719DO. Q.

A vaporizing coibustor vith doable combustion spacesA81-17827

DDGAH, D. C.The JtY-15 tilt rotor research aircraft

A81-16588DOULAT. H. J., JB.

Airspace analysis in airport system planning481-18052

DOBSTOH, O. A.Experimental aerodynamic characteristics of tvo

V/STOL fighter/attack aircraft configurations atBach numbers from 0.4 to 1.1[SASA-TB-81234] N81-1U981

EAVES, A. 7.Coatings in the aero gas turbine

A81-17167BD1ABDS, B. G.

An investigation into grid patching techniguesN81-14708

BD8ABDS, V. B.Helicopter propulsion system development and

qualification481-17511

EHBBHBEEGEB. L. J.Clear air turbulence: Historical comments

H81-11562BBLBBS, B.

Eguipment for testing and measuring a "helmet. mounted sight and display" system vith a coupled

movable television camera in theflight-simulator for research of the DFVLR[DFVLB-HITT-80-04] H81-13960

EILISOH, I. A.An overviev - 1980 generation avionic developments

481-18061BHDBBS, J.

Aviation meteorology research and development: 4status report

H81-14557EPPLBB, B.

4 computer program for the design and analysis oflov-speed airfoils, supplement[HASA-TB-81862J H81-13921

BBDSAHH, F.Eguipment for testing and measuring a "helmet

mounted sight and display" system vith a coupledmovable television camera in theflight-simulator for research of the DPVLB[DFVLR-BITT-80-04] H81-13960

BBBABT. B. G.The XV-15 tilt rotor research aircraft

481-16588EBICKSOH, J. C., JB.

Further investigations of adaptive-vall wind tunnels[4D-4091774] N81-13977

ETTIiGBB, B. C.The implications of current flight controlresearch and development

481-16578BTTLBS, C. a. B.

The rigidity and performance of a simple spiralbevel helicopter gearbox[AS8E PAPER 80-C2/DET-103] 481-18654

BVASS, B. J.Helicopter sarvivability in overvater situations

481-18081

FADDEH, D. B.Computer generated displays and pilot effectiveness

481-18082FAGOT, B.

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] N81-14300

FAIi, B. L.Bunvay Configuration Management System concepts

A81-18089FAIBCBH.D, J. E.

4 pure direct force/moment control for coaxialcounterrotating rotors

H81-15007FAB, F.

An aerodynamic design method for transonic axialflov compressor stage

A81-17805FAB, B.

Airspace analysis in airport system planning481-18052

FAHG, B. T.Geometric dilution of precision in GlobalPositioning System navigation

481-18100PABBELL, C.

Full potential solution of transonic quasi-3-0flov through a cascade using artificialcompressability[HASA-TM-81637] N81-14980

FBBBBBKABP, L. G.Surface finishing[HASA-CASE-BSC-12631-3] N81-14077

FEIBBBT, J. I.Leading-edge deflection optimization for a highly

svept arrov ving configuration[NASA-TP-1777] N81-14974

FEBBIS, B.Safety considerations for helicopter drive systemsof the 1980s

A81-17510FIRE, D. A.

Vanadium trineodecanoate promoter forfiberglass-polyester soil surfacings[AD-4091785] N81-14084

FIBSCHEIH. O.Sutonoaous navigation using passively sensedterrain images

481-17977FITZGEBALD, P. C.

Advanced transmission component development andtest program

481-17507FLEDBT, C.

Dual methods and approximation concepts instructural synthesis[8ASA-CB-3226] H81-14347

FLOIBBS, G. L.Tool force evaluation of lathe machined highexplosives[ HHSHP-80-20] H81-15148

FOBBBB, I.The effect of aerodynamic coupling on the dynamicsof aircraft in fast rolling motion

A81-17471FORBES, B. C.

4 simple combustor system for a small gas turbineengine

481-17503FOBGAS, J. A.

Airport visual approach, guidance and landingsystems - Airline pilots viewpoint

A81-18083

B-1

PESS014L ADTHOH IHDEI BITFIELD, J. J.

FOBSBT, C. R.An investigation into grid patching techniques

881-11708FODGBiEB. J. I., JR.

Passive control of wing/store flutter[HASA-TH-81865] H81-13922

FOOBB, C.Aircraft engine programs employing cost objectives

A81-19346FBOST, B.

Proceedings: Fourth Annual Rorkshop onMeteorological and Environmental Inputs toAviation systems[HASA-CP-2139] N81-14555

Survey of Workshops on Meteorological andEnvironmental Inputs to Aviation Systems

N81-14556FOLLBH, H. C.

The rating of helicopter noise: Development of aproposed impulse correction[NPL-AC-93] 1181-14792

GAJERSSI, T.Conditions of generation and methods of damping

the inlet vortex of a turbojet engineA81-19442

GALLAGHER, M. K.Technological forecasting—aircraft design.Citations from the International Aerospace database[NASA-CB-163833] N81-13957

GAIGLOFF, B.Helicopter alarms - The use of ALAT incident and

accident record cardsA81-16689

SABDBEB, G. F.Advanced transmission component development and

test programA81-17507

SATIBEAO. R. J.History of flight testing the L-1011 Tristar jettransport. I - The L-1011-1

A81-17976GAODETTE. B. P.

Service life determination for the OH-60-A (DTTAS)helicopter elastomeric bearings[AD-A0917S6] N81-14324

GE. S.Structural analysis of fuselages with cutouts byfinite element method

A81-17816GBGEBLE, J.

Visual systems at Lufthansa's simulator centreA81-19199

GEBHABT. P. H.Finite element analysis of inviscid subsonic

boattail flow[NASA-TH-81650] N81-14977

GERSBBEIH. B. A.Laminar boundary layer on swept-back wings of

infinite span at an angle of attackA81-17656

GBRIB. B. L.F-111 windscreen machining[Y-2232] H81-14995

SILLFILLAB, I. E.Southern California aviation system study[PB80-215544] H81-13916

SIRS, J. 0.Statistical relationship between median visibility

and conditions of worstcase manmade impact onvisibility[LA-OB-80-2485] N81-14550

GHELIH, B.Problems of flight mechanics involved inall-weather helicopter operation

A81-1746760BDEL, B.

Active control of an explosive wing-store fluttercase[MBB-FE-17/S/POB/25] H81-13973

GOFF. R. C.Hinds and wind shear in-situ sensors

H81-14563

GOLBIfZ, I. C.Time dependent Navier-Stokes solution of aturbulent gas jet ejected from a rectangularorifice into a high-subsonic crossflow

N81-14964COLDBin, L. B.

Southern California aviation system study[PB80-215544] N81-13916

GOLOBISSKII. A. I.Hypersonic gas flow over a delta wing

A81-19632GOREIKOV. A. F.

Comparative evaluation of the quality of jet fuelsA81-17371

GBAHGIBB. H.Primary training of military pilots - changingtheories and new trainers

A81-19498GBIGOLL, D.

Influence of free-stream turbulence intensity onheat transfer in the two-dimensional turbulentboundary layer of an accelerated compressible flow

A81-17994GROdLI, J. I.

Advanced Attack Helicopter /YAB-64/ - Status reportA81-16580

GROHRALD, A. J.Evaluation of a computer-generated perspective

tunnel display for flight path followingCHASA-TP-1736] H81-13958

GOLDBB, t.Sealing joints and cracks, thin resurfacing, andlocating voids under concrete slabs[PB80-215635] N81-14182

GDPIA, H. K.Frequency-shaped cost functionals - Extension oflinear-quadratic-Gaussian design methods

A81-18578

HBAASZ. A. A.

Aircraft annoyance evaluations using field andlaboratory simulation techniques[UTIAS-248] H81-15580

HABEBCOB, G. E., JR.Maneuvering aircraft: Noise pollution andcontrol. Citations from the NTIS data base[PB80-815566] H81-14525

BAERTIG, J.Application of optical methods to the study of jet

noise and turbulence[ ISL-CO-201/80] H81-15819

HABBI. C. I.Bind shear systems integration plan, VICOH (visualconfirmation) reliability analysis[PB80-218233] N81-13949

BABBL, P.Problems of flight mechanics involved inall-weather helicopter operation

481-17467HABiA, R. F.

A cockpit view of advanced airline avionicsA81-16585

BAISAH. M. J.Autonomous navigation using passively sensed

terrain imagesA81-17977

BABE, B. E.Non-destructive pavement evaluation

A81-18062HABBOLD, H. C.

General Electric infrared suppressors for theBlack Hawk helicopter

481-17520BASBIHOTO, H.

An investigation of support-interference effects[NAL-TB-622] H81-14984

BASSELBOT, A.Downwash calculation at close range behind atrapezoidal winq in supersonic flow[FFA-TH-AD-1661] N81-13925

HATFIELD, J. J.Evaluation of a computer-generated perspectivetunnel display for flight path following[SASA-TP-1736] N81-13958

B-5

BAIBAHB-BABBB, 6. PEESOHAL AOTBOB IBDEI

HAIBABH-BABEB, G.Comparison of experimental and computational shock

structure in a transonic compressor rotor[ASHE PAPEB 80-GT-81] A81-17953

HAYBIB, A. T.Development of a computer program data base of a

navigation aid environment for simulated IFEflight and landing studies[NASA-TB-80064] 1181-13959

BEFPEBHAH, J. T.Surface finishing

[NiSA-CASE-SSC-12631-3] H81-11077HEIBEB, B.

Prestressed concrete airfield pavementsA81-18063

BEBBI, B. A.Vanadium trineodecanoate pronoter for

fiberglass-polyester soil snrfacings[AD-A091785] 881-14081

BBBBBBT. I.Dialogue on bridging some gaps in stability and

transition researchA81-18105

BEBTHICB. B.A summary of proposals for airflight research by

the BHFTA81-19298

HISCBBT. a. J.Heave instabilities of amphibious air cushion

suspension systems[UTIAS-246] H81-15156

BIBOTASO. B.An experimental study on kerosene-hydrogen hybrid

combustion in a gas turbine combustorA81-17841

BISCOCKS, B. D.i case study in aircraft design: The de Havilland

family of STOL commuter aircraftA81-16717

BODGE, B. J.Design of the new Tehran International Airport

A81-18084BOBHLIB6EB. H.

Active flutter suppression on an F-4F aircraftuith external stores using already existingcontrol surfaces[HBB-FE-17/S/POB/24] H81-13972

Active control of an explosive wing-store fluttercase[BBB-FE-17/S/PUB/25] N81-13973

BOFFBAB, S.Bibliography of Supersonic Cruise Research (SCB)

program from 1977 to mid-1980[BASA-BP-1063] H81-14973

BOFHAHB, I.The collision course: Conditions, guidance laws

and properties[DFVLB-FB-80-06] H81-13942

HOGG. G. B.Issues regarding A r m y turboshaft engines

diagnostics and condition monitoringA81-17514

BOGLUBD. L. E.Static source locations for four nozzles mounted

on a J-85 engine[HASA-CB-152401 ] 881-14998

BOLT, A. P., JB.A survey of new technology for cockpit application

to 1990's transport aircraft simulators[NASA-CB-1S9330] H81-11993

BOBBEB, B. 8.Development of high-temperature turbine subsystem

technology to a technology readiness status,phase 2[FE-1806-72] M81-11332

BOBSTBAHB, K. B.Reduction of profile drag by bloving out through

peg holes in areas of streamline separationbubbles[DGLB PAPEB 80-103] A81-19392

BOSBT, H. B.Aerodynamic stability analysis of SASA

J85-13/planar pressure pulse generatorinstallation[NASA-CB-165141] H81-15004

TF34 engine compression system computer study[NASA-CB-159889] N81-15005

HOOSBB, H. 3.Fuel injector characterization studies

[HASA-CH-165200] B81-15003BOIT, J.

Saudi Arabia's new Gateway AirportsA81-18093

BOZOHI, K.An investigation of support-interference effects

[NAL-TB-622] N81-14984BSIB, C.-C.

Hodeling of the terminal area Air TrafficBanagement and Control

A81-18085HD, Z.

A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-17824The measurement and analysis of station parametersof a turbojet engine

A81-17825BOABG, B.

Grid generation for general three-dimensionalconfigurations

N81-14714BDFFSAB, J. K.

Leading-edge deflection optimization for a highlyswept arrow wing configuration[NASA-TP-1777] N81-14974

HDLIH, P. B.Computer Generated Imagery (CGI) current

technology and cost measures feasibility study[AD-A091636] H81-15729

BOHBEL, D.Drag reduction through formation flight

[DGLB PAPEB 80-106] A81-19393SUBLET. J. F.

Advanced technology turboshaft IB suppressionA81-17519

BUSTED, F.Advanced technology tnrboshaft IB suppression

A81-17519BDTSOI, B. B.

UK pavement design and evaluation - A new approachA81-18076

ISBII, S.A study of air breathing rockets - subsonic mode

combustion[IAF PAPEB 80-F-270] A81-18371

ITABCBOK. S. A.Detection of moving objects

A81-18773

JACOB, K.Experimental investigation of a right angle wing

vith partially separated flow with and withoutground effectsC D G L B PAPER 80-111] A81-19397

JiBES, L. L.Omega - An economic Loran A replacement

A81-18077JABESOB, A.

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] H81-14986

JiSIK, S.Digital control for helicopter powerplants

A81-17S04JAIK, T.

Volumetric pattern prediction of antennas onaircraft using the geometrical theory ofdiffraction[ DFVLB-FB-80-01] H81-14195

JIABG, 3.The matrix analysis of wings

A81-17818JOBABSSOB, B. C. A.

The velocity induced by the wake of a wind turbinein a shear layer, including ground effect[FFA-TH-HD-2189-PT-3] B81-14985

JOBS, A. J.The rating of helicopter noise: Development of a

proposed impulse correction[BPL-AC-93] B81-14792

B-6

PBBSOBAl AOIHOB IHDEI LALETIB, K. H.

JOHHSOH. J. B.A resin injection technique foe the fabrication of

aero engine conposite components[PSB-90024] 881-11004

JOHBSOS, B. E.Automating airborne company communications

A81-18061JOBBSXOB. G- i.

Sound radiation from a finite length unflangedcircular duct with anifors axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712Aircraft annoyance evaluations using field and

laboratory simulation techniques[OTIAS-218] H81-15580

JOLZBB. B. S.Airspace simulation in airport system planning

481-18086JOHBS, D. J.

Transonic azisyametric bodies with minimal wave dragA81-17018

JOBBS, E. B.Airline flight departure procedures - Choosing

between noise abatement, minimum fuelconsumption and minioun cost

A81-17011JOHBS. R. B.

A resin injection technigne for the fabrication ofaero engine composite components[PHB-90021] B81-11001

JOSSSThe annoyance caused by noise around airports

[BASA-TM-75781] H81-15579JOD, 8. H.

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] H81-11986

JOTBAS. B.Supersonic stall flutter of high speed fans

tHASA-TB-81613] B81-11978

KKADOTA. I.

An experimental study on kerosene-hydrogen hybridcombustion in a gas turbine combustor

A81-17811KABBBB, B.

The practical application of the lake BlockingCorrections according to Haskell[DS1B PAPEB 80-112] A81-19398

EABL, F.Botor model for verification of computation methods

[ISD-262] N81-15467KAiAEATA. H.

Hodel-following system with assignable errordynamics and its application to aircraft

A81-18577KBBBBDI. T. I.

An evaluation of wind tunnel test technigues foraircraft nozzle afterbody testing at transonicBach numbers[AD-A091775J B81-13931

KETTLES. J. C.Helicopters - Help for the all weather terminal

A81-18065KHAIH07ICH, I. A.

Badio navigation for aircraft: HandbookA81-18599

EBAB. I. A.Vector and scalar characteristics of opposing jets

discharging normally into a cross-streamA81-17997

KBABITOBOV, A. 8.The influence of flow disturbances on the

laminar-turbulent transition in a supersonicboundary layer

A81-19613KIBBAPPBL. f.

Analysis of unsteady pressure measurements on anaerofoil section with an harmonicallyoscillating, slotted flap[DFVLR'FB-80-22] B81-13929

KIBG, B. B.The wear of PTPE-containing dry bearing liners

contaminated by fluids[ASLE ?BEPBIHT 80-LC-6B-3] A81-18758

KIBZLBB, J. A.Surface finishing

[BASA-CASE-BSC-12631-3] H81-11077EITCBBBS, P. t.

Aircraft icing instrumentation: Dnfilled needsB81-11560

ELASS, P. 3.Solid-state power system use expands

AS 1-19191EOBDSIBSEI, V.

Turbopropeller engine PZL-10SA81-17321

KOYASA, I.An investigation of support-interference effects

[SAL-TB-622J 881-11981KBAOS, I.

Computational aerodynamic design tools andtechniques used at fighter development[HBB-PE-122/S/POB/13] B81-13950

KBEIB, S. B.Joint-laboratory qualification testing of oils for

gas turbine enginesA81-17375

EBEISSBLHBIBB, G.Application of vector performance optimization to

a robust control loop design for a fighteraircraft[DPVLB-FB-80-11] B81-13970

KRUTKO, P. D.Inverse problems of controlled flight dynamics -

Longitudinal motionA81-16968

KDBHB, B.Active control of an explosive wing-store flutter

case[HBB-FE-17/S/POB/25] B81-13973

KOBHBBBLB, I.Botor model for verification of computation methods

[ISD-262] B81-15167KOBIBA. B. A.

Composition of sludge formed in B-3T oilAS 1-17373

KOBZ, B.Computational aerodynamic design tools and

technigues used at fighter development[MBB-FE-122/S/POB/13] H81-13950

KOBTBBBACB, F. J.Plight evaluation of a simplified gross thrust

calculation technique using an F100 turbofanengine in an F-15 airplane[BASA-TP-1782] B81-15000

KOSAKIi, S. I.Characteristics of the velocity field near a

wing-body combination located at an angle ofattack to an oncoming supersonic flow

A81-19337The coordinate-deformation method in the problemof a supersonic gas flow over an airfoil

A81-19631KBZHIiSKII, V. A.

Hall cooling and the laminar-turbulent boundarylayer transition at supersonic flow velocities

A81-19611KOZHBISOT. T. G.

Composition of sludge formed in B-37 oilA81-17373

LACEBI, I. B.Organic compounds in the exhaust of a J85-5turbine engine[AD-A091712] B81-13966

LAIBD, C.Hechanisms of damage accumulation intime-dependent cyclic deformation[DOE/EB-10570/1] H81-11363

LAKSHHIHABAIABA, B.Structure and decay characteristics of turbulence

in the near- and far-wake of a moderately loadedcompressor rotor-blade[ASSE PAPER 80-GT-95] A81-17951

LALETIB. E. B.Practical aerodynamics of the helicopter Hi-6A

A81-18600

B-7

LABB, g. PEBSOBAL ADTBOH IIDBI

LABB, B.Mind- tunnel measurements and comparison vith

flight of the boundary layer and heat transferon a hollow cylinder at Hach 3[HASA-TP-1789] B81-14975

LAHBBai. B.Fighters for the 1990s

A81-19497LAHCASTEB, J. K.

The wear of PTFE-containing dry bearing linerscontaminated by fluids[ASLE PBEPBIBT 80-LC-6B-3] A81-18758

LEE, K. D. iGrid generation for general three-dimensional

configurationsH81-1117114

LEE, ¥. S.Surface finishing

[HASA-CASE-HSC- 12631-3} US 1-11*077LBIIIBGBB, e.

Application of the HHA design method to anonlinear turbofan engine[HASA-CB-163855] H81-15001

LBHSKI, J. I., JB.Drive system development for the 1980's

A81-17508LBOHABD, A.

Vottex methods for two- and three-dimensional flowsimulations

H81-15313LEIdAH, C. S.

Concorde aerodynamics and associated systemsdevelopment

A81-16718LI, C.-H.

On the steady state and dynamic performancecharacteristics of floating ring bearings[ A S H B PAPEH 80-C2/LOB-17] A81-18671

LI, P,Experimental investigations on shock-associated

noiseA81-17735

LI, »,A preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

A81-17824LIAPISA. O. A.

Experimental investigation of orographic waves andvertical motions in the Krasnovodsk airport area

A81-19441LIGHT, L.

Dynamic characteristics of a high-speed rotor withradial and axial foil-bearing supports[ASME PAPEB 80-C2/LOB-35] A81-18683

LIB. C.Second order approximation theory of an arbitrary

aerofoil in incompressible potential flowA81-17803

Aerodynamic calculations and design of subcriticalaerofoils

A81-17804LIB, Q.

A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-17821The measurement and analysis of station parameters

of a turbojet engineA81-17825

LID. C.An optimum design procedure of total-temperature

thermocouple probesA81-17807

LID, G.Variational principles and generalized variational

principles for the hybrid aerodynamic problem ofairfoil cascades on an arbitrary stream sheet ofrevolution

A81-17741LID, a.

An experimental investigation of the rotatingstall, surge, and wake behind the rotor for asingle stage axial compressor

A81-17826LID, S.

An aerodynamic design method for transonic axialflow compressor stage

A81-17805

A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-1782UThe measurement and analysis of station parameters

of a turbojet engine&81-17825

LID, S.An experimental investigation of the rotatingstall, surge, and wake behind the rotor for asingle stage axial compressor

A81-17826LOEHB, B.

Equipment for testing and measuring a "helmetmounted sight and display" system with a coupledmovable television camera in theflight-simulator for research of the DFYLBC DFVLB-BITT-80-04 ] H81-13960

LOTZE, A.Effects of nonlinearities on wing store flutter[HBB-FE-17/S/POB/27] N81-13974

LDCAS, E. J.Evaluation of wind tunnel nozzle afterbody testtechniques utilizing a modern twin enginefighter geometry at Hach numbers from 0.6 to 1.2[AD-A091545] H81-13932

LOBHOS, J. B.Experimental aerodynamic characteristics of two

V/STOL fighter/attack aircraft configurations atHach numbers from 0.4 to 1.4[HASA-TB-81234] H81-14981

LOIOBI, J. L.A system for aerodynamic design and analysis ofsupersonic aircraft. Part 2: User's manual[HASA-CB-3352] H81-13920

A'system for aerodynamic design and analysis ofsupersonic aircraft. Part 1: Generaldescription and theoretical development[HASA-CB-3351] H81-14970

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 3: Computer programdescription[HASA-CB-3353] H81-14971

LOO, S.Finite difference computation of the steady

transonic potential flow around airplanesA81-17802

MBA, 0.

Experimental investigations on shock-associatednoise

A81-17735BABBI. D. 6.

The resonance frequencies of ventilated wind tunnels[ABC-H/H-3841] S81-15009

BACE, B. B.Periodically stiffened fluid-loaded plates. I -Besponse to convected harmonic pressure and freewave propagation. II - Besponse to line andpoint forces

A81-17067HACGLASBAH, I. F.

Power control for hot gas engines[HASA-CASE-BPO-14220-1] H81-14318

HACK, J. C.Drive system development for the 1980's

A81-17508Experience with advanced high performance gear steel

[ASHE PAPEB 80-C2/DET-77] A81-186B8BACLBOD, B. I.

Low-speed wind-tnnnel tests of two weathercockingsensors[SSBL-0171-TH] B81-14575

HACPHEBSOB,. P. B.Water content of helicopter gear oils

[ASBE PAPEB 80-C2/DET-12] A81-18640The rigidity and performance of a simple spiral

bevel helicopter gearbox[ASBE PAPEB 80-C2/DET-103] A81-18654

BIGBAB, A.Bird flight and airplane flight

[BASA-TH-75777] H81-14962BAIO, 0.

Performance evaluation of an interrogation-replyscheduling technigne for a discrete addressbeacon system

A81-19U17

B-8

PERSOMAL 10THOB ISDEI 8YBBS, B. D.

DaLISHBV, V. T.Formation of solid phase daring the heating of jet

fuelsA81-17372

BARKOB. B. J.Bunny rehabilitation, lashington National Airport

A81-18066BABTIH, C. L.

Organic compounds in the exhaust of a J85-Sturbine engine[AD-A091712] H81-13966

BABTIB, J. I.Shipboard trials of the Quiet Short-Haul Research

Aircraft /QSRA/A81-16581

BASOIA, e.A study of air breathing rockets - subsonic mode

combustion[ IAF PAPEE 80-P-270] A81-18371

BATHB1S, D. C.Improved methods for fan sound field determination

[NASA-CR-165188] N81-15769BATSOZAKI. T.

An investigation of support-interference effects[NAL-TR-622] N81-14984

BATIBI. a. D.Inlet flow distortion in turbomachinery

[ASBE PAPER 80-GT-20] A81-17952BIOK, S. C.

Remotely piloted vehicles. Citations from theInternational Aerospace abstracts data base[NASA-CR-163864] N81-14996

Lightning. Citations from the InternationalAerospace abstracts data base[NASA-CR-163857] N81-15648

Clean air turbulence. Citations from theInternational Aerospace Abstracts data base[NASA-CR-163863] N81-15649

flCCABB. L. B.The importance of 'Interim Standard Bicrowave

Landing System1 for small community airportsA81-18087

aCCARTBT. J.Doctor Pujita 's aicroburst analysis at Chicago

H81-14572BCDBDE, J. B.

Development of a computer program data base of anavigation aid environment for simulated IFRflight and landing studies[NASA-TB-80064] H81-13959

HCFARLABD, B. B.Solution of plane cascade flow using in proved

surface singularity methods[NASA-TB-81589] N81-14979

HCBILLAH. J. D.Catalog of sea state and wind speed in the South

Atlantic Bight[HASA-CR-156872] H81-11601

BEAD. U H.The Grumman Aerospace and Gulfstream American

Gulfstream III case study in aircraft designA81-16720

BBHU. J. P.A new system for the study of visual information

presentation in aeronautics - GIBIA81-16688

BEBCBB, J. B.Development of finite-volume methods for

three-dimensional transonic flows[AD-A090829] H81-14986

BERIIH, J. T.Southern California aviation system study

[PB80-215544] H81-13916BBIEB. B. I.

Prediction of sound radiated f rom differentpractical jet engine inlets[BASA-CR-163824] N81-14789

BIDDLETOH, i. D.A system for aerodynamic design and analysis of

supersonic aircraft. Part 2: User's manual[HASA-CB-3352] H81-13920

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 1: Generaldescription and theoretical development[SASA-CB-3351] S81-14970

A system for aerodynamic design and analysis ofsupersonic aircraft. Part 3: Computer programdescription[NASA-CB-3353] N81-14971

BIKHALBV, I. A.Principle for the design of hybrid control systems

for passenger transport systemsA81-17577

BILES. J. H.Analysis of pressure spectra measurements in a

ducted combustion system[NASA-TB-81583] H81-15768

BIBBCK, B. S.Hind-tunnel test of an articulated helicopter

rotor model with several tip shapes[8ASA-TS-80080] N81-13918

BISKABAB, I.Sealing joints and cracks, thin resurfacing, and

locating voids under concrete slabsCPB80-215635] 1181-14182

BIOBA. S.Aeronautical-Saritime Engineering Satellite /ABES/

program of Japan[IAF PAPEB 80-D-171] A81-18318

BOAVBBZADEH. F.Runway rehabilitation, Washington National Airport

A81-18066BOH», J. B.

Improved capabilities to detect incipient bearingfailures[AD-A091687] N81-14325

BOLL, T. B.Active flutter suppression on an F-4F aircraft

with external stores using already existingcontrol surfaces[MBB-FE-17/S/PDB/24] N81-13972

BOIAGAB, S. J.Head-tJp-Display flight tests

A81-16582BOOB, 0. A.

Air traffic management enhancement through newavionics /4-D/

A81-16583BORIKAiA, H.

Aeronautical-Baritime Engineering Satellite /AMES/program of Japan[IAF PAPER 80-D-171] A81-18318

BORIBOTO, S.Aeronautical-Baritiue Engineering satellite /ABES/

program of Japan[IAF PAPEB 80-D-171] A81-18318

BORKO7IH, B. T.Dialogue on bridging some gaps in stability and

transition researchA81-18105

BOHLAH, S.Pyrotechnics serving safety

A81-19348BOBTOH. T. 6.

The digital control system as part of anintegrated accessory fit for future engines

A81-17505BOSS, a. j.

Advanced flight deck/crew station simulatorfunctional reguirements[NASA-CR-159331] N81-14994

BROTEK, Z.Map-type displays

A81-19443BDELLEB, B.

Rotor model for verification of computation methods[ISD-262] N81-15467

HOEBSCHER, D.A contribution to stabilization of flight vehicle

parachute systems[DFVLR-MITT-80-05] N81-13926

BOLCAI, I.Rotary balance data for a single-engine

agricultural airplane configuration for anangle-of-attack range of 8 deg to 90 deg[NASA-CB-3311] N81-13923

BOBDIE, D. L.Transonic axisymmetric bodies with minimal wave drag

A81-17048BDRPBI, L. D.

Southern California aviation system study[PB80-215544] H81-13916

BIBBS, B. D.Community participation in airport planning

A81-18067

B-9

BAKASUBA, H. PBBSOHAL iDTBOB IgDEI

NHAKABOBA, H.

& method foe obtaining shockless transonic flowspast airfoils, partially modified fcon a givenarbitrary airfoil[HAL-TB-602T] N81-14983

HAHDOBI, V. G.Application of fracture mechanics in designing

lover wing skin of transport aircraft481-170119

BAOCK, J.Sarsat - A rescue system for ships and aircraft

A81-16684HBISB. 8.

Noise and noise abatement in fans and blowers: Areview[DFVLH-FB-80-16 ] H81-14796

NEKBASOTA. H. B.Some characteristics of snbsonic flow over the

root area of a sveptback wingA81-19633

HELBS, B. P.Experinental aerodynamic characteristics of tvo

V/STOL fighter/attack aircraft configurations atMach numbers from 0.4 to 1.4[SASA-TB-81234] H81-14981

BBPPEBT, B.Drag estimations for stream-line and cylindrical

contour distortions on aircraft fuselages andtrain cars[DGLB PAPEB 80-116] A81-19399

HE1IOB, A. G.The fu ture of civil tarbo-fan engines

[PNB-90034] N81-13964HIELSEH, J. P.

Becent developments in NOT techniquesA81-18078

HIGBO, 0. B.Gas turbine engines and transmissions for bus

demonstration programs[COO-4867-07] H81-14329

BIKOLSKII. A. A.Plane vortex gas flows

A81-19634BISHT, B. I.

Nonlinear aerodynamic characteristics of a thinairfoil of arbitrary plane configuration

A81-19629NIXOB, 0.

Development of finite-volume methods forthree-dimensional transonic flows[AD-A090829] N81-14986

BOCBOBSOB. D.Statistical relationship between median visibility

and conditions of worstcase manmade impact onvisibility[LA-DB-80-2485] N81-14550

MOHBAKEB. D. O.A survey of new technology for cockpit application

to 1990's transport aircraft simulators[NASA-CB-159330] N81-14993

HOBTOH. P. S.Planning for and evaluating the potential of a

land based aircraft for carrier operationsA81-19470

NOfOSABTOV, G. T.Composition of sludge formed in B-3V oil

A81-17373Joint-laboratory gualification testing of oils for

gas turbine enginesA81-17375

OBBAZTSOV, I. F.The method of superelements in the dynamics of

complex structuresA81-16969

OSIHOTO. K.Sound radiation f rom a finite length nnflanged

circular duct with uniform axial flow. I -Theoretical analysis. II - Computed radiationcharacteristics

A81-16712

OKOBB07, B. 8.Principle for the design of hybrid control systems

for passenger transport systemsA81-17577

OLIVES. B. J.L-1011 Flight Hanageaent system design

considerationsA81-18074

OIO, K.The effect of cyclic loading on the apparentcleavage fracture toughness of 1cr-Bo-V rotorsteel

A81-17488OPDIKE, G., JB.

A siiple combnstor system for a small gas turbineengine

A81-17503OSIPOI, A. A.

Propagation of three-dimensional acousticperturbations in channels of variablecross-sectional area at frequencies close tocutoff frequency

A81-19338

PACKBB, L. L.Improved capabilities to detect incipient bearingfailures[AD-A091687J N81-14325

PAILHAS. G.Beview of theoretical and experimental results onthree dimensional turbulent wakes and boundarylayers[OHEBA-NT-1980-4] H81-13930

PAPIB, J. P.Helicopter alarms - The use of ALAT incident andaccident record cards

A81-16689PAHKBB. B. J.

Performance of computer-optimized tapered-rollerbearings to 2.4 million DN[ASBB PAPEH 80-C2/LOB-18] A81-18672

Lubrication of rolling element bearingsA81-18738

PABE, P.Current aircraft survey (approach speeds, gross

weights, and Dimensions)[PB80-225691] N81-13956

PATEL, T. S.Optimum selection of main parameters for thereverse design of a supersonic military aircraft

A81-17047PATTOS. J. H.. JB.

A status report on NASA general aviationstall/spin flight testing

A81-19471PEISIS, S. T.

Laminar boundary layer on swept-back wings ofinfinite span at an angle of attack

A81-17656PBBKS, B. P.

The digital control system as part of anintegrated accessory fit for future engines

A81-17505PEBSOOB, A. J.

Transonic wind tunnel tests on an oscillating wingwith external store. Part 4: The wing withunderwing: Store[AD-A077370] 881-14969

PETEBSEH, J. C.A computer-based laser Doppler velocimeter[DF7LB-HTTT-79-14] B81-14289

PETBOT, B. B.Inverse problems of controlled flight dynamics -

Longitudinal motionA81-16968

PFEIFFEB, H. J.An analytic aodel of subsonic flow around anairflow with a spoiler

N81-14966PIIEL. S. I.

Performance of computer-optimized tapered-rollerbearings to 2.4 million DH[ASBE PAPEB 80-C2/LOB-18] A81-18672

PISABO, A. 0.Failure Indication and Corrective Action for

turboshaft enginesA81-17515

B-10

PEBSOBAL AOTHOB ISDBI BOOS, B.

PLATSBK. B. B.Airport/environs plan making - Hanaging the

planning process481-18088

POCOCK, C. L.Turbulence: From a pilot's viewpoint

H81-14561POCOCE, e.

Ferrography as a health monitor and a design aidfoe the developnent of helicopter gearboxes

181-18759P08STEOKE, B.

Transonic wind tunnel tests on an oscillating vingKith external store. Part 4: The wing withonderwing: Store[AD-A077370] H81-14969

POLIAKBOV, I. B.Stead; flow past a rectangular wing with

circulation that is variable along the spanA81-16551

POLL, 0. I. A.Three-dimensional boundary layer transition via

the mechanisms of 'attachment linecontamination' and 'cross flow instability'

A81-18122PBICB, I. L.

Laser-Baman/Bayleigh flow diagnostic techniquesapplied to subsonic flow[AD-A091695] H81-14275

PBIIOLO. B. F.The coordinate-deformation method in the problem

of a supersonic gas flow over an airfoilA81-19631

PDBSBL, B.Flight test investigation of LOBAS-C for en route

navigation in the Gulf of Mexico[AO-A091637] H81-13945

POZTBEVSU, B.Some aspects of optimizing the aerodynamics of

turbine stagesA81-19325

QQIAB, B.

Finite difference computation of the steadytransonic potential flow around airplanes

A81-17802QUASI, A.

Reduction of profile drag by blowing out throughpeg holes in areas of streamline separationbubbles[DGLH PAPER 80-103] A81-19392

Laminar-airfoils for transport aircraft[DFVLB-BITT-80-07] H81-13952

QOIRBI. 6. t.An assessment of General Aviation utilization of

advanced avionics technologyCNASA-CB-159328] H81-13941

BABE, D, C.Effects of downstream distance on turbulence decayfor the compressor research facility lowconditioning system[AD-A091543] H81-14276

HADFOBD. B. C.Landing flying qualities evaluation criteria for

augmented aircraft[NASA-CE-163097] N81-13969

BA6BOHATHAB, S.A study of multiple jets

A81-18024BAGOLIB, B. t.

Rail cooling and the laminar-turbulent boundarylayer transition at supersonic flow velocities

A81-19644BAO. D. H.

Aerodynamic side-force alleviator means[HASA-CASE-LAB-12326-1] H81-14968

BAPBAEL. D. E.Aviation assumptions in the eighties

A81-18068BATTEBBBB, B. L.

Fully bonded concrete overlay for an airport runwayA81-18075

BADCB, B. B.Improved ceramic heat exchanger materials

[HASA-CB-159678] M81-14082BAVIIDBABATfl, A.

Structure and decay characteristics of turbulencein the near- and far-wake of a moderately loadedcompressor rotor-blade[ASBE PAPER 80-GT-95] A81-17954

BAT, 6. K.Sealing joints and cracks, thin resurfacing, and

locating voids under concrete slabs[PB80-215635] H81-14182

BE, B. J.Investigation of convergent-divergent nozzles

applicable to reduced-power supersonic cruiseaircraft[NASA-TP-1766] 881-14972

BECB, J.Concorde aerodynamics and associated systems

developmentA81-16718

SEED, B. E.Microwave landing systems. Citations from the

Engineering Index data base[PB80-814643] N81-13947

Microwave landing systems. Citations from theNTIS data base[PB80-814635] N81-13948

BEEO, 8. B., IllPassive control of wing/store flutter

[HASA-TS-81865] N81-13922BEICBEB1, G.

Hingeless tailrotor in fiber compositeconstruction and vibration-isolation systems/ARIS, ASIS/ for helicopters[HBB-OD-311-80-0] A81-19300

BEID, I. H.A study of eultiple jets

A81-18024BICBABDSOH, A.. Ill

Organic compounds in the exhaust of a J85-5turbine engine[AD-A091712] N81-13966

BICKETTS, B. A.Effects of angle of attack and ventral fin on

transonic flutter characteristics of anarrow-wing configuration[NASA-TH-81914] H81-15397

BIECKBOF, B.-J.Automatization of the adhesion process for

supporting airframe parts in light contour systemsA81-19297

BIFPEL, B. E.Experimental determination of unsteady blade

element aerodynamics in cascades. Volume 2:Translation mode cascade[NASA-CB-165166] N81-14976

BIX, 0.System identification of the longitudinal motion

of the DFVLR HFB 320 research aircraft withparticular consideration of control surfaceeffectiveness[DFYLH-HITT-79-16] H81-13971

BOBEBTSOH. J. B.Evaluation of a computer-generated perspective

tunnel display for flight path following[NASA-TP-1736] N81-13958

BOBIHSOH, C. A., JR.Industry proposes supersonic V/STOL

A81-19490BOBIHSOH, 0. I.

The rating of helicopter noise: Development of aproposed impulse correction[HPL-AC-93] H81-14792

BOBOB, S. B.On the steady state and dynamic performance

characteristics of floating ring bearings[ A S M E PAPER 80-C2/LOB-17] A81-18671

ROHAH, I.The effect of cyclic loading on the apparent

cleavage fracture toughness of 1Cr-Ho-V rotorsteel

A81-17488BOOS, B.

Transonic wind tunnel tests on an oscillating wingwith external store. Part 4: The wing withunderwing: Store[AD-A077370] H81-1U969

B-11

BOSEITI. C. PEBSOBAl AOTBOB IIDBI

BOSBTTI, C.Satellites to aid flight safety

[ IAF PAPEB 80-IAA-17] A81-18410BOTHBOCK, B. 0.

Experimental determination of unsteady bladeelement aerodynamics in cascades. Volume 2:Translation mode cascade[NASA-CB-165166] 1181-14976

BOTBSCHILD. S. I.The future ATC system as influenced by advanced

avionicsA81-16586

BOOBD. D. P.Analysis of unsteady pressure measurements on an

aerofoil section with an harmonicallyoscillating, slotted flap[DFVLB-FB-80-22] H81-13929

EOZBDESTVESSKII. K. T.Determination of the effect of transverse cutouts

on the hydrodynamic characteristics of afinite-span wing in the case of steady andunsteady motion near a vail

A81-19335BOBBEBT, P. E.

Grid generation for general three-dimensionalconfigurations

S81-1U714BOEBB, I. C.

Curved centerline air intake for a gas turbineengine[BASA-CASE-LEH-13201-1] N81-14999

BOPPE, J. P.Today and the future in aircraft wheel and brake

developmentA81-17046

arm, H. j., JB.A new perspective in aviation systems planning

&81-18069

SACBEH, P.Computational aerodynamic design tools and

techniques used at fighter development[HBB-FE-122/S/POB/13] H81-13950

SACHS, G.The effect of aerodynamic coupling on the dynamics

of aircraft in fast rolling motionA81-17471

SAKA, H.Prevention of spline vear by soft metallic coatings

[AD-A091861] H81-14064SALIABIS, C.

A contribution to stabilization of flight vehicleparachute systems[DFVLB-HITT-80-05] S81-13926

SALHIBS, S.Avionics and displays in a future airspace system

A81-18070SABDLIB, O. B.

Flight evaluation of the terminal guidance system[HASA-CB-163859] N81-11991

SAHTOCCI, 6. F.A nev system for the study of visual information

presentation in aeronautics - GIBIA81-16688

SAVA, P. e.The Dalembertometer

[ISL-CO-220/79] N81-14292Application of optical methods to the study of jet

noise and turbulence[ISL-CO-201/80] H81-15819

SCABLOI. J.The problems of helicopter ditching

A81-18071SCBAFBABEK. D.

Theoretical investigation of the influence ofspoiler dynamics on the handling qualities of anaircraft with direct lift control[DFVLB-FB-80-07] H81-13975

SCBIATO. A.Fuel conservation in the air transportation

industry - General and operational aspectsA81-17143

SCBIJVB. J.Prediction methods for fatigue crack growth in

aircraft materialA81-18777

SCBBIDT, D.A fault tolerant nnltiprocessor system with

reconfiguration suitable for multiaxial flightstabilization and trimming

A81-19296SCBHIDT, G. 1.

Crnise-missile-carrier navigation requirementsA81-18576

SCHBIT, L. A., JB.Dual methods and approximation concepts in

structural synthesis[HASA-CB-3226] B81-14347

SCBHItf, C. F.. JB.Captive carry and free flight rain erosion

considerations for reinforced ablativefluorocarbon badome materials

A81-17453SCBIIPPEBS, P.

Transonic wind tunnel tests on an oscillating wingwith external store. Part 4: The wing withunderwing: Store[AD-A077370] H81-14969

SCHBOEBS, L. G.The XV-15 tilt rotor research aircraft

A81-16588SCHOBEBT, H.

Applicated techniques for the control of approachtraffic[DFVLB-HITT-79-20] N81-14992

SCBDLLEB, F. T.Calculated and experimental data for a 118-am bore

roller bearing to 3 million DH[ A S H E PAPER 80-C2/LOB-14] A81-18668

SCBIEIBOLD. F. J.Development and operational flight test of the

model 250-C28B gas turbine engineA81-17512

SBIDBL. B. S.Inlet flow distortion in tnrbouachinery

[ASBE PAPEB 80-GT-20] A81-17952SEHPLE, ». G.

An economic and versatile panel method foraircraft and aircraft/store configurations. Anoutline of the principal features of themathematical modeling and numericalimplementation of the British Aerospace (Barton)Sk II Panel Method

N81-15311SEiSBOBG, O.

Active flutter suppression on an F-4F aircraftwith external stores using already existingcontrol surfaces[HBB-FE-17/S/PUB/24] B81-13972

Active control of an explosive wing-store fluttercase[HBB-FE-17/S/PDB/25] H81-13973

Effects of nonlinearities on wing store flutter[HBB-FE-17/S/PDB/27] H81-13974

SBTTEBLOBD. B. B.Cruise-missile-carrier navigation reguirements

A81-18576SEIELL, C.

Circulation Control ling /CC»/ flight testsA81-19469

SEIPBIED, A.Applicated techniques for the control of approach

traffic[DFVLB-BITT-79-20] B81-14992

SBCHEDBIH, A. I.Hypersonic gas flow over a delta wing

481-19632SHESTEBHISA, t. H.

Steady flow past a rectangular wing withcirculation that is variable along the span

A81-16551SBOBIH, T. P.

Elimination of vibrations in aircraft piping systemsA81-18497

SBVALEV, 10. G.Rail cooling and the laminar-turbulent boundary

layer transition at supersonic flow velocitiesA81-19644

SIDEHSTICK, J. E.Turbine blade technology - Present and future

[ A S H E PAPEB 80-C2/AEBO-10] A81-18639

B-12

PEBSOBAt AOTHOB IHDEI TATB, J. L.

SIEBEBT, C. H.Transonic wind tunnel tests on an oscillating ving

vith external store. Part 4: The wing withunderving: Store[AD-A077370] 881-11(969

SIGBBfl. B. B.Performance of computer-optimized tapered-roller

bearings to 2.1 million DM[ASSE PAPEB 80-C2ADB-18] A81-18672

SIB, 8. C.Prevention of spline vear by soft metallic coatings

[AD-A091B61] 881-14064SIHCtAIB. 0. I.

Laser-Baman/Rayleigh flov diagnostic techniguesapplied to subsonic flov[AD-A091695] 881-14275

SIBBi. A. B.Bunvay Configuration Management System concepts

A81-18089SIPPEL. K. 0.

Constant-amplitude and flight-by-flight tests onCEBP specimens[HBB-FE-2/S/POB-26] 881-14006

SLIIi, S. H.Economic evaluation of flying-qualities design

criteria for a transport configured vith relaxedstatic stability[NASA-TP-1760] B81-13968

SalGIKLSKI, P.The Dalembertooeter

[ISL-CO-220/79] 881-14292Controls of aeronautical structures under fatigue

testing by holographic pulsed lasersinterferometry[ISL-CO-218/79] N81-11300

SS1TB. E. B.Carved centerline air intake for a gas turbine

engine[BASA-CASE-LEH-13201-1] 881-14999

SNUB. B.Landing flying qualities evaluation criteria for

augmented aircraft[HASA-CB-163097] H81-13969

SUITS, B. E.Bead-Dp-Display flight tests

A81-16582SHITB, B. K.

Development and certification of the Gulfstream IIIA81-16587

SOFIBV, E. I.Experimental investigation of orographic vaves and

vertical motions in the Krasnovodsk airport areaA81-19441

SOFBIB, I. 6.Improved methods for fan sound field determination

[8ASA-CB-165188] 881-15769SOBERS. D. H.

A computer program foe the design and analysis oflov-speed airfoils, supplement[NASA-TB-81862] 881-13921

SOBBLEIIIBB, I.The determination of the induced drag on slim

Kings vith high lift systems in the transonicregion[HBB-FE122] A81-19400

SOSBOYSKU, A. A.Badio navigation for aircraft: Handbook

A81-18599SOOTHBBH. I. S.

Exhaust noise in flight: The role of acousticinstallation effects[PBB-90029] B81-14793

SPIKES, H. A.Rater content of helicopter gear oils

[ASHE PAPEB 80-C2/DET-12] A81-186UOSTALLIHGS, B. L., JB.,

Sind-tunnel measurements and comparison vithflight of the boundary layer and heat transferon a hollow cylinder at Bach 3[SASA-TP-1789] 881-14975

STEABBAB, B, O.The effects of warhead-induced damage on the

aeroelastic characteristics of lifting surfaces.Volume 1: Aeroelastic effects[AD-A091674] B81-13955

STEE8KE8, H. S.Aerodynamic stability analysis of BASA

j85-13/planar pressure pulse generatorinstallation[BASA-CH-165141] B81-15004

TF34 engine compression system computer study[BASA-CB-159889] 881-15005

STBIBBAOSEB, B.Application of vector performance optimization to

a robust control loop design for a fighteraircraft[DFVLB-FB-80-14] 881-13970

STEPBBBS. 6. E.Cost/benefit analysis of advanced materials

technologies for future aircraft turbine engines[SASA-CB-165225] B81-15006

STEVBBS, B.Supersonic stall flutter of high speed fans

[BASA-TK-81613] 881-14978STIHPFLIBG, A.

Controls of aeronautical structures under fatiguetesting by holographic pulsed lasersinterferometry[ISL-CO-218/79] 881-14300

STBAKOSCB. J.The Grumman Aerospace and Gulfstream American

Gulfstream III case study in aircraft designA81-16720

STBAOB, J.Influence of free-stream turbulence intensity on

heat transfer in the tvo-dimensional turbulentboundary layer of an accelerated compressible flov

A81-17994STHICKLABD, P. B.

Shipboard trials of the Quiet short-Haul ResearchAircraft /QSHA/

A81-16581SIBOBG, B. E.

Compressor configuration and design optimizationfor the high reliability gas turbine[DOE/ET-15332/11] B81-15414

STOCKAS, K. J.Advanced Technology Spark-Ignition Aircraft Piston

Engine Design study[BASA-CB-165162] B81-13963

SOB, I. P.Prevention of spline vaar by soft metallic coatings

[AD-A091861] 881-14064SOLTiS, S. H.

Traffic forecasting for the BfilAA81-18090

SOHIBSKI, L. I.. JB.Computer Generated Imagery (CGI) current

technology and cost measures feasibility study[AD-A091636] B81-15729

SDH, C.Structural analysis of fuselages vith cutouts by

finite element methodA81-17816

SZODBOCB, J.Experimental study of supersonic viscous leeside

flov over a slender delta wing[SASA-TH-81248] B81-14265

TABA, H. B. A.The rigidity and performance of a simple spiral

bevel helicopter gearbox[ASHE PAPER 80-C2/DET-103 ] A81-18654

TABS, 0.A preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

A81-17824TABS, B.

A vaporizing combustor vith double combustion spacesA81-17827

TABS, X.Structural analysis of fuselages vith cutouts by

finite element methodA81-17816

TASSIBABI, H.The design-to-cost of aircraft

A81-19344TAIB, J. L.

Advanced flight deck/crev station simulatorfunctional requirements[HASA-CB-159331] 881-14994

B-13

TBBBOiB. G. PBBSOBAL AOTHOH IIDEI

TBBHUBB, G.Flight instramentation reqnireients for

all-weather approach and landingA81-18059

TEBSEIKB, T. S.The method of superelements in the dynamics of

complex structuresA81-16969

IEIBLHAH. A. S.The effect of cyclic loading on the apparent

cleavage fracture toughness of 1Cr-Mo-V rotorsteel

A81-17488TBBB, D. I.

Advanced ejection seat for high dynamic pressureescape. Hind tunnel test[AD-A091810] H81-139UO

THOHBT. a. A.Traffic forecasting for the HBIA

A81-18090IHOBPKIIS. B. T.. JB.

Comparison of experimental and computational shockstructure in a transonic coapressor rotor[ASBE PAPER 80-GT-81] A81-17953

TBOBBTOH, J. B.Sealing joints and cracks, thin resurfacing, and

locating voids under concrete slabs[PB80-215635] N81-14182

TIJDEHAH. H.Transonic wind tunnel tests on an oscillating wing

with external store. Part 4: The King withunderwing: store£»D-A077370] H81-11969

TODA, 4.Approximation of gear transmission error by

standard gear errors[&SBE PAPEB 80-C2/DET-71] A81-18646

TOBDIOB. G. T.Approximation of gear transmission error by

standard gear errors[&SSE PAPEB 80-C2/DET-71] A81-18646

TOBEHBEEK, B.Fundamentals of conceptual design optimization of

subsonic transport aircraft[VTH-LB-292] H81-13951

TBIJ08IS. J.Statistical relationship between median .visibility

and conditions of vorstcase manmade impact onvisibility[LA-UH-80-2485] . N81-11550

IBITEDI. K. S.

Validation Methods Besearch for Fault-TolerantAvionics and Control Systems Sub-Dorking GroupBeeting. CABE 3 peer review[NASA-CP-2167] N81-15702

TDCKBB, B. T.Canada's national aviation forecasting models

A81-18072TDJAKA, S.

Collisions between aircraft and birdsA81-19445

TOBCZEBIBK, B.Exhaust gas reingestion ueasurements

A81-17521TDBE. B.

Experimental investigation of a right angle wingwith partially separated flow with and withoutground effects[DGLB PAPEB 80-111] A81-19397

liJGGS, I. E.

757/767 design considerations for improvedproductivity

A81-1658I1TiOBBI. B. J.

Beview of engine/airframe/drive train dynamicinterface development problems

A81-17516

uUIGDB. E. B.

Nondestructive dynamic testing

VALOT, C. L.A new system for the study of visual informationpresentation in aeronautics - GIBI

A81-16688VAI UFFBLBB, J. P.

Characteristics of HAVSTAB user stationsA81-19125

Hill, A. S.Aerial surveying of small areas froi a small

remotely controlled droneA81-17525

YAIIDIBB, J. I. G.Transonic wind tunnel tests on an oscillating wing

with external store. Part 4: The wing withnnderwing: Store[AD-A077370] N81-14969

7AOCBEBET, X.Model vibrations beyond low-speed stall

A81-19552VAOSHA8. t. W.

Aeronautical concerns and National Aeronautics andSpace Administration atmospheric electricityprojects

H81-11567VOELCKEBS, 0.

Applicated techniques for the control of approachtraffic[DFVLB-BITT-79-20] H81-14992

VOLHIB, A. S.The method of superelements in the dynamics ofcomplex structures

A81-16969

w

A81-19657

IADIA, A. B.A pure direct force/moment control for coaxial

counterrotating rotorsH81-15007

1AGBEB, O.The supercritical profile of the supercritical wing

A81-17522BALKEB, J. E.

A case study on the F-16 fly-by-wire flightcontrol system

A81-16719IALI, B. L.

Advanced flight deck/crew station simulatorfunctional requirements[HASA-CB-159331] N81-11991

IALLBB, B. A.Environmental aspects of airport planning

A81-18091IALIBOOB. L.

A • s u r v e y of new technology for cockpit applicationto 1990's transport aircraft simulators[HASA-CE-159330] N81-14993

IAB6, D.Finite difference computation of the steady

transonic potential flow around airplanesA81-17802

IABG. B.Experimental investigations on shock-associated

noiseA81-17735

iAIG, z.A preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

A81-17824The measurement and analysis of station parameters

of a turbojet engineA81-17825

iATAHABE, T.Aeronautical-Baritiae Engineering satellite /AaES/

program of Japan[ I A F PAPEB 80-D-171] A81-18318

BBBBB, O.flidair and near midair collisions on two- and

three-dimensional curvilinear flight paths[DFV1B-FB-80-13] H81-13944

BEOAB, B. I.Beasuring weather for aviation safety in the 1980's

H81-11568

B-11

PBBSOIU. 40IHOB IIDBI ZHOU, I.

IEDBKZB0. 6.Calculation of the lift dependent drag polar of

cambered fighter plane configurations withdeflected maneuver flaps in the subsonic regionby Beans of a nodified procedure according toLanar[DGLB PAPEB 80-109] 481-19395

Procedures for optimal drag design of camber andflap deflection in supersonic regions vithconsideration to geometric limits[DGLB PAPEB 80-110] A81-19396

1ED6B. B. B.Coatings in the aero gas turbine

A81-17167BBBBBB, B. P.

Computer generated displays and pilot effectivenessA81-18082

HBIHBBJCB, B.-l.One-dimensional considerations concerning the

stability behavior of inlet diffnsers forsupersonic aircraft

A81-17548RBISGBBBBB, D.

Constant-amplitude and flight-by-flight tests onCEBP specimens[8BB-FE-2/S/POB-26] H81-14006

•BSLBB, J. B.The federal role in airport noise control planning

A81-18073iEVBBS, L. J.

Experimental analysis and methods to determine thedynamic behavior of propulsion shafting systems

H81-15401IBITB. P. C.

The role of aircraft separation assurance in thecockpit

481-18092•BITE, 6.

4 low height 2300 kW helicopter transmission Kithan enclosed planetary gear[ASHE PAPER 80-C2/DET-17] A81-18642

BHITBLAB, J. B.Vector and scalar characteristics of opposing jets

discharging normally into a cross-stream481-17997

ilUIAHS. D. t.Testing model rotorcraft for overvater operations

481-180588ILLI4MS. i. D.

Laser-Baman/Rayleigh flow diagnostic techniquesapplied to subsonic flov[AD-A091695] S81-14275

ilLLSHlBE, I. L.. JB.Assessment of ground effects on the propagation of

aircraft noise: The 1-384 flight experiment[HASA-TP-1747] H81-14788

BinLIFF, C. B.Further investigations of adaptive-vall wind tunnels

[AD-A091774] H81-13977BOODBAS, A. L.

Vanadium trineodecanoate promoter forfiberglass-polyester soil snrfacings[AD-A091785] H81-14084

•BICBT, F. F.L-1011 Flight Management System design

considerationsA81-18074

BO. I.A preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

A81-17824The measurement and analysis of station parametersof a turbojet engine

A81-17825

ID. I.The matrix analysis of wings

A81-17818

IAH6. Q.The automatic matrix force method and technigues

for handling more complex computations vithgiven computer capacity

A81-17815

IB. T.Structural analysis of fuselages vith cutouts by

finite element methodA81-17816

TOSBIZABA. A.An investigation of support-interference effects

[BAL-TH-622] 581-1198"IOSO, J.

An experimental study on kerosene-hydrogen hybridcombustion in a gas turbine combnstor

481-17841lOSt, S. B.

DC-to-DC pover supply for light aircraft flighttesting[S4SA-CB-163850] H81-14989

100. S.The measurement and analysis of station parameters

of a turbojet engineA81-17825

TODS6BAHS. J. L.Curved centerline air intake for a gas turbine

engine[NAS4-CASE-LEB-13201-1] N81-14999

TO. J.4 preliminary experimental investigation of the

response of a turbojet engine to inlet pressuredistortion

481-17824TO, I. J.

Gcid generation for general three-dimensionalconfigurations

N81-14714IOBCZIK. B. F.

Advanced ejection seat for high dynamic pressureescape. Hind tunnel test[AD-A091810] M81-13940

ZABABAKBIH, B. I.Stationary displacement of a body by a shock vave

481-17622ZABABAKBIH, H. B.

Stationary displacement of a body by a shock vaveA81-17622

ZBABG, C.An experimental investigation of the rotatingstall, surge, and vake behind the rotor for asingle stage axial compressor

A81-17826ZHASS, B.

An experimental investigation of the rotatingstall, surge, and vake behind the rotor for asingle stage axial compressor

481-17826ZBAO. 3.

An optimum design procedure of total-temperaturethermocouple probes

A81-178074 preliminary experimental investigation of theresponse of a turbojet engine to inlet pressuredistortion

481-17824The measurement and analysis of station parametersof a turbojet engine

A81-17825ZflBH, I.

Finite difference computation of the steadytransonic potential flov around airplanes

A81-17802ZBBBG, L.

The measurement and analysis of station parametersof a turbojet engine

481-17825ZBIGDLBV, T. H.

Thin minimum-drag airfoils481-19630

ZHI1IH, ID. L.The sonic boom from an aircraft flying along anarbitrary path in a stratified atmosphere in thepresence of a three-component vind

481-19636ZBOO, I.

An aerodynamic design method for transonic axialflov compressor stage

481-17805

B-15

ZBD, t. PBBSOIAL ADTBOB IIDEX

SHO. f.An aerodynamic design method for transonic axialflow compressor stage

A81-17805SHO, a.

A vaporising combastor Kith doable combustion spacesA81-17827

KBD, 8.The matrix analysis of wings

A81-17818ZBDLISA. 10. v.

Detection of moving objectsA81-18773

ZIHH, B. T.Prediction of sound radiated from different

practical jet engine inlets[NASA-CR-16382«] H81-1«789

ZOLLA8S, G. F.Aircraft maintenance. Citations from the

International Aerospace Abstracts data base[NASA-CB-163837] 881-13917

Technological forecasting—aircraft design.Citations from the International Aerospace database[NASA-CB-163833] B81-13957

B-16

CONTRACT NUMBER INDEXAERONAUTICAL ENGINEERING IA Continuing Bibliography (Suppl. 134)

Typical Contract Number Index Listing

APRIL 1981

HASl-16000 H81-11013

CONTRACTNUMBER

NASA ACCESSIONNUMBER

Listings in this index are arranged alphanumerically by contract number.Under each contract number, the accession numbers denoting documentsthat have been produced as a result of research done under that contractare arranged in ascending order with the IAA accession numbers appearingfirst. The accession number denotes the number by which the citation isidentified in either the fAAor STAR section.

4F PBOJ. 2301N81-13955

&F PBOJ. 2U02N81-13940

AF PBOJ. 3018N81-14325

AP PBOJ. 3066N81-14276

4F PBOJ. 7351N81-1U061

AF PROJ. 7930H81-13966

AF-AFOSB-3233-77N81-14969

AF-AFOSB-3569-78N81-13955

BHFT-ET-4086-AN81-15467

DAAG46-78-C-0030N81-14324

DAAJ02-77-C-0037A81-17516

DE-AC02-78CS-54867N81-14329

DE-AC02-80EB-10570N81-14363

DE-AC03-79ET-15332N81-15414

DE-AC03-79ET-15425H81-14327

DE-AC04-76DP-00487H81-15148

DE-AI01-77CS-510I10N81-14082

DOT-FA79HA-4184A81-18089

DOT-FA79WA-4279N81-13949

EC-77-A-31-1011H81-14082

EJ-76-C-01-1806N81-14332

FAA PBOJ. 015-390-130N81-13915

FSV-F-K-80123-78-017-21-001K81-13925

F33615-76-C-5191N81-14061

F33615-78-C-1563A81-18576

F33615-78-C-2008N81-14325

F33615-79-C-3106N81-139I10

F33657-78-C-0473A81-18576

F10600-78-C-0003N81-13977

F19620-77-C-013A81-18105

F49620-77-C-0066N81-1II789

SAG1-70 H81-15702HAG3-67 N81-1I1789HASA OEDEB L-11593

N81-13941

NASU-3198NASB-3199NAS1-1U849HAS1-1553U

HAS1-15546

N81-15579N81-1U962N81-13923N81-13920H81-14970N81-14971H81-la993H81-14994N81-14998N81-14082H81-14976H81-15006881-15005H81-15004N81-13963N81-15003N81-15769H81-13969A81-18100N81-14601M81-1t555N81-14985

NAS2-9399SAS3-19698SAS3-20055SAS3-20072NAS3-20599SAS3-21259NAS3-21272HAS3-21288NAS3-21391KAS4-2534SAS5-24300HAS6-2639BAS8-32692NE-5061-013NGL-22-009-383

A81-17953SGB-39-009-017

N81-14989NSEBC-A-7945 A81-16712HSG-1490 H81-14347NSG-3012 A81-17954NSG-3171 N81-15001NSG-3189 A81-17952NSG-4022 N81-14991H00014-76-C-0068

H81-14064H00014-77-C-0247

A81-18578S00014-78-C-0079

N81-14986S61339-79-D-0008

N81-15729PBOJ. AFS-560-79-17

N81-13956B-7U05-EHG-26

N81-14995U-7405-ENG-36

N81-14550501-31-33-05 N81-13921505-04-82 H81-14977505-06-64 H81-13969505-10-13-16 N81-13923505-32 N81-14980505-32-03-01 N81-14788505-32-13-01 N81-14972505-33-53-01 N81-13922505-33-63-02 N81-14347505-34-23-01 H81-13958505-34-33-05 N81-13968505-34-43-05 H81-15702505-41-73-01 H81-13959

H81-14997505-42-71 H81-14981505-43-23-02 H81-14975505-51-11 H81-14265506-51-34 S81-15000533-01-13-07 N81-15397533-01-43-01 H81-14973533-01-43-02 N81-14974

1. Report No.

NASA SP-703703^)

2. Government Accession No. 3. Recipient's Catalog No.

4. Title and Subtitle 5. Report Date

Apr i l 1981

AERONAUTICAL ENGINEERING

A Continuing Bibliography (Supplement6. Performing Organijation Code

7. Author(s) 8. Performing Organization Report No.

10. Work Unit No.

9. Performing Organization Name and Address

National Aeronautics and Space AdministrationWashington, O.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

10. Abstract

This bibliography lists 387 reports, articles, and other documentsintroduced into the NASA scientific and technical information systemin March 1981.

17. Key Words (Suggested by Author(s))

AerodynamicsAeronautical EngineeringAeronaut icsBi bliograph ies

18. Distribution Statement

Unclassi f ied - Unlimited

19. Security Classif. (of this report)

Unclass i fied

20. Security Classif. (of tr.:; page)

Unclassi f ied

21. No. of Pages

117

22. Price*

$5.00 HC

For sale by the National Technical Information Service, Springfield, Virginia 22161NASA-Lanpley, 1981

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