CForm Approved REPORTDOCUMENT _ __ _PGE OMB No. 0704-0 8 -i rd trt~r~r~ ? ' ta n O.Me. 'Ins C ' ng, itv na 'vo-rq t?-e ntV ot -1: -ao na : em -'a .t ts b ,.j ~r'aeV t o~ ~ 'n, 1-4tior, o 1 O -c: c o irt -,,,qto ouce ]C urir s '-~~.- - - ' , ci5 oiirs.ia - :is . . ., t n 12C4 .. ' -ltOn . '. V1d."2 i-a t jf,.e )t M,,Cne-eit tr C nc oer-c, '_, ' 324nt ", . 1. AGENCY USE ONLY ,heave olank) j2. REPORT DATE j 3. REPORT TYPE AND DATES COVERED I Mkrrh 1QQlI Paper Jan 89 - Sep 89 14. DTLE AND SUBTITLE 5. '"NDIN-G NUMBERS 0 Thin-Layer Navier-Stokes Solutions of the Asymmetric ! PE: 61102F Vnrtirul Flnw nn A Tmnnan+ fniva RndW PR: 2307 AUTHOR(S) TA: El WU: 26 O AFATL Program Manager: Kirk J. Vanden PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION NREPORT NUMBER ~ Aerodynamics Branch Aeromechanics Division Air Force Armament Laboratory (AFATL/FXA) AFATL-TP-90-04 O--I Eqlin Air Force Base, FL 32542-5434 _ SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONS iI AGENCY!ER'N R ":',-. ,,= 21990 I'. fUPPLEMENTARY NOTES 2..i,..;o; This paper was not edited nor published by AFATL/D01R. 12-. UISTRIBUTION'AVAILABILITY STATEMENT 12b. DISTRIBUTION CODE Approved for public release; distribution is unlimited ! '. ,.35TRACT f.klax~rrn urn 200 wordls) q -- " 2 Laminar solutions for asymmetric vortical flow on a five caliber tangent ogive with an eight caliber cylindrical afterbody were calculated with a thin-layer Navier- Stokes code on a one block algebraic grid. Solutions were obtained for Mach 1.4 at 25, 30, 37.5, 38.5, and 40_degeesanglet of attack. The Reynolds number for all cases was 200,000 based on lthV maximum body diameter. Two-dimensional particle traces in cross-sections of the flow and the limiting streamlines were calculated from the solutions. (The validity of the thin-layer approximation in the flow field far away from the boundary layer was studied by recomputing the 37.5 degt'ee case with the viscosity turned off at a distance away from the body. The solution was not significantly different, indicating that the outer vortex flow is basically inviscid.- Both symmetric and asymmetric cases were calculated and analyzed. "The secondary flow was shown in detail. "The complexity of the, secondary flow increased with angle of attack. 2, Crossflow topology diagrams were given in detail for symmetric and asymmetric conditions to illustrate the fundamental difference between L OBJECT TERMS "5 NUMBER (2F PAGES I 16. PRICE CODE SECURITY CLASSIFICATION 18. SECURITY CLASSIFICATION 19 SECURITY CLASSIFICATION 20. LIMITATION OFABSTRACT )F 1E PORT C AOF THIS PAGE OF ABSTRAC2 Hli -CIATFTFDJ I II AqfTPTFfn I lINCI ASCTFTFFn gad •0 0,,2 107 9 0 0 4 1 ,'....., '.... .. . .
This document is posted to help you gain knowledge. Please leave a comment to let me know what you think about it! Share it to your friends and learn new things together.
Transcript
CForm Approved
REPORTDOCUMENT _ __ _PGE OMB No. 0704-0 8
-i rd trt~r~r~ ? ' ta n O.Me. 'Ins C ' ng, itv na 'vo-rq t?-e ntV ot -1: -ao na : em -'a .t ts b ,.j ~r'aeV t o~ ~'n, 1-4tior, o 1 O -c: c o irt -,,,qto ouce ]C urir s '-~~.- - - ' , ci5 oiirs.ia - :is
. . ., t n 12C4 .. ' -ltOn . '. V1d."2 i-a t jf,.e )t M,,Cne-eit tr C nc oer-c, '_, ' 324nt ", .
1. AGENCY USE ONLY ,heave olank) j2. REPORT DATE j 3. REPORT TYPE AND DATES COVERED
I Mkrrh 1QQlI Paper Jan 89 - Sep 8914. DTLE AND SUBTITLE 5. '"NDIN-G NUMBERS
0 Thin-Layer Navier-Stokes Solutions of the Asymmetric ! PE: 61102FVnrtirul Flnw nn A Tmnnan+ fniva RndW PR: 2307AUTHOR(S) TA: El
WU: 26
O AFATL Program Manager: Kirk J. VandenPERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES) 8. PERFORMING ORGANIZATION
NREPORT NUMBER
~ Aerodynamics BranchAeromechanics DivisionAir Force Armament Laboratory (AFATL/FXA) AFATL-TP-90-04
O--I Eqlin Air Force Base, FL 32542-5434 _
SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES) 10. SPONS iIAGENCY!ER'N R
":',-. ,,= 21990
I'. fUPPLEMENTARY NOTES 2..i,..;o;
This paper was not edited nor published by AFATL/D01R.
12-. UISTRIBUTION'AVAILABILITY STATEMENT 12b. DISTRIBUTION CODE
Approved for public release; distribution is unlimited! '. ,.35TRACT f.klax~rrn urn 200 wordls) q
-- "2 Laminar solutions for asymmetric vortical flow on a five caliber tangent ogive
with an eight caliber cylindrical afterbody were calculated with a thin-layer Navier-Stokes code on a one block algebraic grid.
Solutions were obtained for Mach 1.4 at 25, 30, 37.5, 38.5, and 40_degeesangletof attack. The Reynolds number for all cases was 200,000 based on lthV maximum bodydiameter. Two-dimensional particle traces in cross-sections of the flow and thelimiting streamlines were calculated from the solutions.
(The validity of the thin-layer approximation in the flow field far away from theboundary layer was studied by recomputing the 37.5 degt'ee case with the viscosityturned off at a distance away from the body. The solution was not significantly
different, indicating that the outer vortex flow is basically inviscid.-Both symmetric and asymmetric cases were calculated and analyzed. "The secondary
flow was shown in detail. "The complexity of the, secondary flow increased with angleof attack. 2,
Crossflow topology diagrams were given in detail for symmetric andasymmetric conditions to illustrate the fundamental difference between
Hli -CIATFTFDJ I II AqfTPTFfn I lINCI ASCTFTFFn gad
•0 0,,2 1079 0 0 4 1 ,'....., '.... .. . .
V
13. ABSTRACT (CONCLUDED)
thes'e conditions. Asymmetry,..according to this research,, wascharacterized by the change in-the topological structure nearthe saddle point associated with the primary vortices. In ad-dition, the--reation of vortex-by &the, pinching of another vor-tex ,was found to occur. This phenomenon was observed in both
-the primary and secondary flow. K IThe singular points obtained from the two-dimensional par-
ticle traces satisfied the topological summation rule for two-dimensional sections of a three-dimensional flow. The primaryseparation and associated vortices agree qualitatively with ex-perimental data. The secondary separation region, however,contained additional topological structures that have not beenresolved in previous experimental studies.
PREFACE
This paper was prepared by Kirk J. Vanden of the ComputationalFluid Dynamics Section, Aerodynamics Branch, Aeromechanics Divi-sion, Air Force Armament Laboratory, Eglin Air Force Base, Flo-rida. The work was performed under Work Unit 2307E126 during theperiod from January 1989 to September 1989.
This paper presents an investigation of asymetric vorticalflow on a tangent ogive body based upon solutions obtained by athin-layer Navier-Stokes code in use in the Computational FluidDynamics Section.
NTiS '',
J 2' ,
A I
iii/iv (Blank)
TA1BLE OF Cfmf1S
Page
AOWLED1M. ........................................ iv
LIST OF %BLES ............................................ v
LIST OF FIGRES .......................................... vi
KEY 70 SYMBOLS........................................... x
A1A= .................................................. xii
I 1C N ........................................... 1
II FLOW SOLVER ............................................ 5
foci-saddle point amtination is shown in Figure 58. This gives, in the
overall flow, eight nodes, three saddles, and 12 half saddle points.
Substituting into the topology summation equation gives
(7 +) - ( 2 +1). -1'2 -7
again in complete agreement. Figure 59 shows the limiting streamlines on
the rear of the body. They are highly asymmetric and contain a number of
sharp kinks.
Figures 60-64 show the circumferential coefficient of
pressure at X/L=97.0% for all the angles of attack calculated. Theta
equal to zero and 360 correspond to the windward stagnation point. The
direction of rotation is clockwise in relation to the two-dimnsional
streamline calculations previously shown. The symmetric pressure
coefficient distribution agrees qualitatively with Lamont 6 and Ericsson
and Reding3 3 . The bmps in the pressure coefficient at
aprroximtely a theta of 135 degrees for each of the cases correspond to
the portion of the secondary flow with the small vortices nearest the
body. Table 1 gives the forces and moments for all cases calculated.
Since the free stream flow is supersonic the vortex-induced side forces
are smaller than the normal force, agreeing qualitatively with
Lamont 6 , Ericsson and Reciing34 , and Keener 9 et al.
83
-4. . . . . ... ...
84
E0,
L
-40-
9L t
85
cra)
I~- -4
C:))CQ C\Z
86
4r)
0 ./
et,,
C/a
all
to 0
- - .- 4 .-.. "" 4 O.4
. • ----+ S,- I
*1o" s II
/ -m
87
c -4
C44
4r
o to
C'? 4)
cl0 SIp
88
'0 0o4
C)
CD
CL.-
-3)
• ,4 C7%
0
III
60 10
-
89
-4
t 06
C..CV
90
00 0
0 0 1 ~4 V
0*
0. C0
4 '.4 In Inl fn .1 CU..................
CHAPER VI
CC1 CLUSIGNS
Asypmtric vortical flow has been calculated numerically using a
thin-layer Navier-Stokes algorithm. It was found that the thin-layer
aproximation models the physics acceptably in both the boundary-layer
and outer flow regions.
Both symmetric and asymnetric cases were calculated and analyzed.
The secondary flow was shown in detail. The basic structure was found to
agree qualitatively with experimental results, and a number of additional
structures and characteristics were observed. The complexity of the
secondary flow region increased with angle of attack.
Crossf low topology diagrams were given for symmetric and asymmetric
conditions to illustrate the fundamental difference between these
conditions. Asymmetry, according to this research, was characterized by
the change in the topological structure near the saddle point associated
with the primary vortices. In addition, the creation of a vortex by the
pinching of another vortex was found to occur. A saddle point was formed
in the middle of this two vortex structure. This phenomenon was observed
in both the primary and secdary flow.
In general, these results were in qualitative agreement with
experimental data, but showed additional structures not observed
previously.
91
RF CES
I. Keener, E.R., and Taleghani, J., "Wind Tunnel Investigations ofthe Aerodynamic Characteristics of Five Forexody Models at High Angles ofAttack at Mach Numbers from 0.25 to 2," National Aeronautics and SpaceAdministration Technical Mmoradum NASA TH X-73076, December 1975.
2. McElroy, G.E., and Sharp, P.S., "An Aproach to Stall/SpinDevelopment and Test,", American Institute of Aeronautics and AstronauticsPaper AIAA 71-772, July 1971.
3. Mounts, J.S., Belk, D.M., and Whitfield, D.L., "Program EAGLE -Users's Manual Volume IV: Multi-block, Implicit, Steady-State EulerAlgorithn," Air Force Armament Laboratory Technical Report AFATL-88-117,September 1988.
4. Chapman, G.T., 'Nonlinear Problems in Flight Dynamics," NationalAeronautics and Space Adinistration Technical Memrandum NASA-TM-85940,May 1984.
5. Legendre, R., 'Separation de 1'Ecoulement LaminaireTridimensional," La Recherche Aeronautique, No. 54, pp. 3-8, November-Deomter 1956.
6. Lamont, P.J., "Pressure Measur~nents on an Ogive Cylinder at HighAngles of Attack with Laminar, Transitional, or Turbulent Separation,"American Institute of Aeronautics and Astronautics Paper AIM 80-1556,1980.
7. Yanta, W.J., Wardlaw, A.B., and Sternklar, D., "Vortex AsymmetryDevelopment on a Tanget Ogive," Naval Surface Weapons Center TechnicalReport NSWC 82-394, October 1982.
8. Keener, E.R., "Flow-Separation Patterns on SymmetricForebodies," National Aeronautics and Space Administration TechnicalMauorancbkn NASA T-86016, January 1986.
9. Keener, E.R., Chapman, G.T., and Kruse, R.L., "Effects of MachNu ber and Afterbcdy Length on Aerodynamic Side Forces at Zero Sideslipon Symmetric Bodies at High Angles of Attack," American Institute ofAeronautics and Astronautics Paper AIAA 76-66, January 1976.
10. Keener, E.R., and Chapman G.T., "Onset of Aerodynamic SideForces at Zero Sideslip on Symmetric Forebodies at High Angles ofAttack," American Institute of Aeronautics and Astronautics Paper AIAA74-770, August 1974.
92
93
11. Peake, D.J., Owen, F.K., and Johnson, D.A., "Control of ForexxlyVortex Orientation to Alleviate Side Forces," American Institute ofAeronautics and Astronautics Paper AIAA 80-0183, January 1980.
12. Fidler, J.E., "Active Control of Asymmetric Vortex Effects,"American Institute of Aeronautics and Astronautics Journal of Aircraft,Volume 18, pp. 267-272, April 1981.
13. Ying, S.X., Schiff, L.B., and Steger, J.L., "A Numerical Studyof Three-Dimnsional Separated Flow Past a Hemisphere Cylinder," AericanInstitute of Aeronautics and Astronautics Paper AIAA 87-1207, June 1987.
14. Siclari, M.J., and Marconi, F., "The Ccmputation of Navier-Stokes Solutions Exhibiting Asymnetric Vortices," American Institute ofAeronautics and Astronautics Paper AIAA 89-1817, June 1989.
15. Whitfield, D.L., "Implicit Upwind Finite Volume Scheme for theThree-Dimensional Duler Epuations," Mississippi State University Report,Mr -ES-ASE-85-1, Sepetrber 1985.
16. Belk, D.M. and Whitfield, D.L., "Tize-Accurate Euler BquationsSolutions on Dynamic Blocked Grids," American Institute of Aeronauticsand Astronautics Paper AIM 87-1127, June 1987.
17. Gatlin, B. and Whitfield, D.L., "An Implicit, Upwind, Finite-Volume Method for Solving The Three-Dimensional Thin-Layer Navier-StokesBEuations," American Institute of Aeronautics and Astronautics PaperAIAA-87-1149, June 1987.
18. Simpson, L.B., "Unsteady Three-Dimensional Thin-Layer Navier-Stokes Solutions on Dynamic Blocked Grids," Ph.D. Dissertation,Mississippi State University, December 1988.
20. Davey, A., "Boundary-Layer Flow at a Saddle Point ofAttachment," Journal of Fluid Mechanics, Volume 10, pp. 593-610, 1961.
21. Lighthill, M.J., "Attachment and Separation in Three-Dimensional Flow," Laminar Boundary Layers, Section II 2.6, L. Rosenhead,ed., Oxford University Press, pp. 72-82, 1963.
22. Smith, J.H.B., "Remarks on the Structure of Conical Flow,"Royal Aircraft Establishment Technical Report RAE TR 69119, June 1969.
23. Perry, A.E., and Fairlie, B.D., "Critical Points in FlowPatterns," Advances in Geophysics, Volume 18B, pp. 299-315, 1974.
I a
94
24. Hunt, J.C.R., Abell, C.J., Peterka, J.A., and Woo, H.,"Kinematical Studies of the Flows Around Free or Surface-MountedObstacles; Applying Topology to Flow Visualization," Journal of FluidMechanics, Volume 86, Part 1, pp. 179-200, 1978.
25. Tobak, M. and Peake, D.J., "Tbpology of Three-DimensionalSeparated Fluid Flows," Annual Review of Fluid Mechanics, Volume 14, pp.61-85, 1982.
26. Sears, W.R., "The Boundary Layer of Yawed Cylinders," Journalof Aeronautical Sciences, Volume 15, Number 1, pp. 49-52, January 1948.
27. Legrdre, R., "Lignes de Courant d'un Etoulement Continu,"Rederche Aerospatiale., Number 105, pp. 3-9, 1965.
28. Thaqpon, J.F., "Program GLE - User's Manual, Volumes II andIII," Air Force Armament Laboratory Technical Report AFATL-TR-88-117,Setmer 1988.
29. Binion, T.W., and Stanewsky, E., "Observed Reynolds NurberEffects: Low Aspect Ratio Wings and Bodies," Advisory Group for AerospaceResearch and Development Conference Proceedings AGARD CP-232, 1989.
30. Walatka, P.P. and Buning, P.G., "PLOT3D User's Manual," NationalAeronautics and Space Administration Technical Memorandum NASA TM-101067,1989.
31. Bouard, R., and Coutanceau, M., 'Mhe Early Stage of Developrentof the Wake Behind an Impulsively Started Cylinder for 40<RE<10,000,"Journal of Fluid Mechanics, Volume 101, Part 3, pp. 583-607, 1980.
32. Peake, D.J., and Tobak, M., "On Issues Concerning FlowSeparation and Vortical Flows in Three Dimensions," Advisory Group forAerospace Research and Dvelopmnt Conference roceedin AGRD CP-342,April 1983.
33. Ericsson, L.E., and Reding, J.P., "Asymmetric Vortex SheddingFran Bodies of Revolution," Progress in Aeronautics and AstronauticsVolume 104, 'Tactical Missile Aerodynamics," American Institute ofAeronautics and Astronautics, 1986.
34. Ericsson, L.E., and Reding, J.P., "Vortex-Induced AsymmetricLoads in 2-D and 3-D Flows," American Institute of Aeronautics andAstronautics Paper AIAA 80-1269, 1980.