1、LOAN COPY: REAFWL TECHNICALK.RTLANDAERODYNAMIC ANALYSESREQUIRING ADVANCEDCOMPUTERSPart IIA conference held atLANGLEY RESEARCH CENTERHampton, VirginiaNATIONAL AERONAUTICS AND SFProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-NASA SP-347TECH LIBRARY KA
2、FB, NMAERODYNAMIC ANALYSESREQUIRING ADVANCEDCOMPUTERSPart IIA conference held atLangley Research Center in Hampton, Virginiaon March 4-6, 1975Prepared by Langley Research CenterScientific and Technical Information Office 1975NATIONAL AERONAUTICS AND SPACE ADMINISTRATIONWashington, D.C.Provided by IH
3、SNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-RC-IevFor sale by the National Technical Information ServiceSpringfield, Virginia 22161Price-$17.25Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-PREFACEThis compila
4、tion consists of papers presented at a conference on AerodynamicAnalyses Requiring Advanced Computers held at the NASA Langley Research Center onMarch 4-6, 1975.The purpose of the conference was to present results of recent theoretical researchon aerodynamic flow problems requiring the use of advanc
5、ed computers. The conferencewas divided into the following sessions: (1) Viscous Flows, (2) Internal Flows, (3) Two-Dimensional Configurations, and (4) Three-Dimensional Configurations. Papers werepresented by members of NASA Centers, Universities, and Industry.iiijProvided by IHS Not for ResaleNo r
6、eproduction or networking permitted without license from IHS-,-,-Page intentionally left blank Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-CONTENTSPart I*PREFACE illCochairmen: Percy J. BobbittVictor L. PetersonAlfred Gessow1. INTRODUCTORY REMARK
7、S 12. REMOTE ACCESS OF THE ILLIAC IV 9K. G. Stephens, Jr.VISCOUS FLOWSStudies Involving Boundary-Layer EquationsChairman: Dennis M. Bushnell3. CALCULATION OF THREE-DIMENSIONAL COMPRESSIBLE LAMINAR ANDTURBULENT BOUNDARY LAYERS 17PREFACE 17Julius E. HarrisAN IMPLICIT FINITE-DIFFERENCE PROCEDURE FOR SO
8、LVING THETHREE-DIMENSIONAL COMPRESSIBLE LAMINAR, TRANSITIONAL,AND TURBULENT BOUNDARY-LAYER EQUATIONS . 19Julius E. HarrisCALCULATION OF THREE-DIMENSIONAL COMPRESSIBLE BOUNDARYLAYERS ON ARBITRARY WINGS . . 41Tuncer Cebeci, Kalle Kaups, Judy Ramsey, and Alfred MoserTHREE-DIMENSIONAL COMPRESSIBLE BOUND
9、ARY LAYERS OFREACTING GASES OVER REALISTIC CONFIGURATIONS 77Robert M. Kendall, William S. Bonnett, Charles T. Nardo, andMichael J. Abbett4. A NUMERICAL METHOD FOR THE PREDICTION OF HIGH-SPEEDBOUNDARY-LAYER TRANSITION USING LINEAR THEORY . 10lLeslie M. Mack*Papers 1 to 22 are presented under separate
10、 cover.Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-5. SOLUTIONS FOR INCOMPRESSIBLE SEPARATED BOUNDARY LAYERSINCLUDING VISCOUS-INVISCID INTERACTION. . . . . . . . . . . . 125James E. Carter and Stephen F. Wornom6. ON THE CALCULATION OF SUPERSONIC
11、SEPARATING ANDREATTACHING FLOWS i .“. 151JohnD. Murphy, Leroy L. Presley, and W. C. Rose7. ASYMPTOTIC THEORY OF TWO-DIMENSIONAL TRAILING-EDGE FLOWS . . 177R. E. Melnik and R. Chow8. ANALYTICAL STUDY OF MIXING AND REACTING THREE-DIMENSIONALSUPERSONIC COMBUSTOR FLOW FIELDS . 251A. J. Baker, R. Clayton
12、 Rogers, and S. W. ZelaznyTurbulence Modeling and Navier-Stokes Equations.Chairman: .Joseph G. Marvin9. SUBGRTO- OR REYNOLDS STRESS-MODE LING FOR THREE-DIMENSIONALTURBULENCE,COMPUTATIONS . . . ! 317 . Morris W. Rubesin . , . . -“,-10. INFLUENCE OF EXTERNAL DISTURBANCES AND COMPRESSIBILITY ONFREE TUR
13、BULENT MIXING . . . . ;. 341Youn H. Oh and-Dennis M;. Bushnell11. AN EXPERIMENTAL AND NUMERICAL INVESTIGATION OF SHOCK-WAVE “INDUCED TURBULENT BOUNDARY-LAYER SEPARATION ATHYPERSONIC SPEEDS . 1 . . . . . . .;. . . . . 377J. G. Marvin, C. C. Horstman, M. W. Rubesin, T. J. Coakley, andM. I. Kussoy. “ p
14、. . ; . .12. CALCULATION OF SHOCK-SEPARATED TURBULENT BOUNDARYLAYERS . . . . . . . .-. . . . . . . . . . .-. . . . V ._; . . 401B. S. Baldwin and W. C. Rose .13. SIMULATION OF TURBULENT TRANSONIC SEPARATED FLOW OVERAN AIRFOIL . . . . . . . . . . . . : . ./. 419George S. Deiwert, John B. McDevitt, an
15、d Lionel L. Levy, Jr.14. AN INVESTIGATION OF SEVERAL NUMERICAL PROCEDURES FOR TIME- -ASYMPTOTIC COMPRESSIBLE NAVIER-STOKES SOLUTIONS . . 437David H. Rudy, Dana J. Morris, Doris K. Blanchard, Charlie H. Cooke,and Stanley G. Rubin . . . . ,viProvided by IHSNot for ResaleNo reproduction or networking p
16、ermitted without license from IHS-,-,-15. NUMERICAL SOLUTION OF THE NAVIER-STOKES EQUATIONS FOR . . ARBITRARY TWO-DIMENSIONAL AIRFOILS . 469Frank C. Thames, Joe F. Thompson, and,C.;Wayne Mastin16. NUMERICAL COMPUTATION OF VISCOUS FLOWS ON THE LEE ,SIDE OFBLUNT SHAPES FLYING AT SUPERSONIC SPEEDS 531J
17、ohn V. RaMch and Stephen C. Lubard .17. CALCULATION OF SUPERSONIC THREE-DIMENSIONAL FREE-MIXINGFLOWS USING THE PARABOLIC-ELLIPTIC NAVIER-STOKESEQUATIONS 543Richard S. Hirsh -INTERNAL FLOWSChairman: Bernhard H. Anderson18. COMPUTATIONAL ASPECTS OF THE PREDICTION OF MULTIDIMENSIONALTRANSONIC FLOWS IN
18、TURBOMACHINERY . 567David A. Oliver and Panagiotis Sparis -19. TIME-DEPENDENT TRANSONIC FLOW SOLUTIONS FOR AXIALTURBOMACHINERY . . 587John Erdos, Edgar Alzner, Paul Kalben, William McNally, andSimon Slutsky T?20. A COMPARISON OF A SHOCK-CAPTURING TECHNIQUE WITHEXPERIMENTAL DATA FOR THREE-DIMENSIONAK
19、 INTERNAL -,FLOWS . . . .ti .I;-. . . 623Leroy L. Presley . 21. INTERNAL AND EXTERNAL AXIAL CORNER FLOWS“ 643Paul Kutler, Vijaya Shankar, Dale A. Anderson, and Reese L. Sorenson22. NUMERICAL METHODS FOR THE CALCULATION OFTHREE-DIMENSIONAL NOZZLE EXHAUST FLOW FIELDS . 659Sanford M. Dash and Paul D. D
20、el GuidiceviiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-Part HTWO-DIMENSIONAL CONFIGURATIONSChairman: Alfred Gessow23. COMPUTERIZED PROCEDURES FOR AIRFOIL DESIGN 703Raymond L. Barger and Cuyler W. Brooks, Jr.24. A COMPUTER PROGRAM FOR THE ANALYS
21、IS OF MULTIELEMENTAIRFOILS IN TWO-DIMENSIONAL SUBSONIC, VISCOUS FLOW . 713Harry L. Morgan, Jr.25. APPLICATION OF NUMERICAL OPTIMIZATION TECHNIQUES TOAIRFOIL DESIGN 749Garret N. Vanderplaats, Raymond N. Hicks, and Earll M. Murman26. TSFOIL - A COMPUTER CODE FOR TWO-DIMENSIONAL TRANSONICCALCULATIONS,
22、INCLUDING WIND-TUNNEL WALL EFFECTS ANDWAVE-DRAG EVALUATION 769Earll M. Murman, Frank R. Bailey, and Margaret L. Johnson27. NUMERICAL INTEGRATION OF THE SMALL-DISTURBANCE POTENTIALAND EULER EQUATIONS FOR UNSTEADY TRANSONIC FLOW 789Richard M. Beam and William F. Ballhaus28. CALCULATION OF INVE3CID SHE
23、AR FLOW USING A RELAXATIONMETHOD FOR THE EULER EQUATIONS 811Joseph L. Steger and Harvard Lomax29. PROGRESS IN APPLICATION OF DIRECT ELLIPTIC SOLVERS TOTRANSONIC FLOW COMPUTATIONS 839E. Dale Martin “THREE-DIMENSIONAL CONFIGURATIONSSubsonic and Supersonic AircraftChairman: Roy V. Harris, Jr. i“ 30. RE
24、CENT DEVELOPMENTS IN PROPULSIVE-LIFT AERODYNAMIC, THEORY 871Richard J. Margason, Long P. Yip, and Thomas G. GainerviiiProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-31. SURVEY OF COMPUTATIONAL METHODS FOR LIFT-GENERATEDWAKES 897Vernon J. Rossow32. S
25、IMULATION OF UNSTEADY THREE-DIMENSIONAL SEPARATED FLOWS. WITH INTERACTING VORTEX FILAMENTS 925A. Leonard33. ADVANCED PANEL-TYPE INFLUENCE COEFFICIENT METHODSAPPLIED TO SUBSONIC AND SUPERSONIC FLOWS 939F. Edward Ehlers, Forrester T. Johnson, and Paul E. Rubberti34. SOME RECENT APPLICATIONS OF THE SUC
26、TION ANALOGY TOVORTEX-LIFT ESTIMATES 985John E. Lamar35. A THREE-DIMENSIONAL SOLUTION OF FLOWS OVER WINGS WITHLEADING EDGE VORTEX SEPARATION 1013James A. Weber, Guenter W. Brune, Forrester T. Johnson, Paul Lu,and Paul E. Rubbert36. ADVANCES IN SONIC BOOM THEORY . . 1033J. L. Lung, B. Tiegerman, N. J
27、. Yu, and A. R. Seebass“37. AN INTEGRATED SYSTEM FOR THE AERODYNAMIC DESIGN ANDANALYSIS OF SUPERSONIC AIRCRAFT “. . . . 1049David S. Miller and Wilbur D. Middleton38. INDICIAL COMPRESSIBLE POTENTIAL AERODYNAMICS AROUNDCOMPLEX AIRCRAFT CONFIGURATIONS 1067;Luigi Morino and Lee-Tzong Chen39. THREE-DIME
28、NSIONAL, SHOCK-ON-SHOCK INTERACTION PROBLEM 1111Paul Kutler and Leonidas Sakell :Transonic AircraftChairman: Jerry C. South, Jr.40. COMPARISONS OF THEORETICAL AND EXPERIMENTAL PRESSUREDISTRIBUTIONS ON AN ARROW-WING CONFIGURATION ATTRANSONIC SPEEDS 1141Marjorie E. Manro, Edward N. Tinoco, Percy J. Bo
29、bbitt, andJohn T. RogersIXProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-41. NUMERICAL MODELING OF TUNNEL-WALL AND.BODY-SHAPE EFFECTS. ON TRANSONIC FLOWS OVER FINITE LIFTING WINGS 1189Perry A. Newman and E. B. Klunker .42. COMPARISONS OF COMPUTED CA
30、ND EXPERIMENTAL PRESSURES FOR . . TRANSONIC FLOWS ABOUT ISOLATED WINGS AND WING-FUSEL AGE :CONFIGURATIONS . . . . .-, . ._. 1213F. R. Bailey and W. F. Ballhaus43. AXISYMMETRIC TRANSONIC FLOW INCLUDING WIND-TUNNEL WALLEFFECTS :. 1233Jerry C. South, Jr., and James D. Keller44. COMPUTATIONAL TRANSONICS
31、 . 1269Paul R. Garabedian45. APPROXIMATE METHOD FOR CALCULATING TRANSONIC FLOW ABOUTLIFTING WING-BODY COMBINATIONS 1281Richard W. Barnwell46. RECENT ADVANCES AND CONCEPTS IN UNSTEADY AERODYNAMICS. . THEORY 1305Samuel R. Bland Space Shuttle .Chairman: Victor L. Peterson47. REACTING NONEQUILIBRIUM FLO
32、W AROUND THE SPACE SHUTTLEUSING A TIME-SPLIT METHOD . . . . . . ; . . 1327Arthur W. Rizzi and Harry E. Bailey 48. COMPUTATION OF SHUTTLE NONEQUILIBRIUM FLOW FIELDS ON APARALLEL PROCESSOR 1351W. C. Davy and W. A, Reinhardt49. FLOW FIELD AND HEATING ON THE WINDWARD SIDE OF THE SPACESHUTTLE ORBITER . 1
33、377John V. Rakich and Eva B. Pegot50. SCALING OF ORBITER AEROTHERMODYNAMIC DATA THROUGHNUMERICAL FLOW FIELD SIMULATIONS 1395W. D. Goodrich, C. P. Li, C. K. Houston, R. M. Meyers, and L. OlmedoProvided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-51. COMPUT
34、ATION OF HIGH-SPEED INVISCID FLOWS ABOUT REALCONFIGURATIONS 1411Frank Marconi, Larry Yaeger, and H. Harris Hamiltoni52. NUMERICAL COMPUTATION OF VISCOUS BLUNT BODY FLOWS WITHA PLANAR IMPINGING SHOCK . . . . 1457Terry L. Hoist, John C. Tannehill, and John V. Rakich xiProvided by IHSNot for ResaleNo r
35、eproduction or networking permitted without license from IHS-,-,-Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-COMPUTERIZED PROCEDURES FOR AIRFOIL DESIGNBy Raymond L. Barger and Cuyler W. Brooks, Jr.NASA Langley Research CenterSUMMARYSeveral airfoi
36、l design procedures are described. The first is a procedure fordesigning an airfoil shape to have a prescribed surface pressure distribution. It isapplicable to the design of supercritical as well as subcritical airfoils. The second is acomputerized procedure based on the Theodorsen e-function desig
37、n technique and isessentially incompressible. It also permits prescription of the pressure distribution,but with the additional feature that it provides simple means of controlling important air-foil parameters. The remainder of the discussion is concerned with the application ofvarious techniques b
38、ased on the e-function theory to specialized design problems.INTRODUCTIONThe inrhouse airfoil design investigation with which this paper is concerned wasinitiated as part of the general airfoil research program at Langley. An interestingaspect of this program is the variety of directions that the de
39、sign problem has taken; forexample, supercritical wing sections, general aviation wing sections, helicopter rotorblades, and “span-loader“ sections. There are also numerous airfoil characteristics,such as design lift coefficient, ideal angle of attack, pitching moment, shape of the pres-sure distrib
40、ution, maximum thickness, and distribution of thickness, that must be con- .trolled in the design process, to a greater or lesser degree, depending on the application.For example, in the design of helicopter rotor blades, a low pitching moment is animportant factor. On the other hand, for general av
41、iation wing sections, the pitchingmoment is not a primary consideration, but such characteristics as the ideal angle ofattack and the design lift coefficient assume a more important role. For supercriticalwing sections, the essential consideration is the shape of the compressible flow pressuredistri
42、bution. For a “span-loader“ section, the pitching moment again becomes importanttogether with such factors as the distribution of thickness and the design lift coefficient.Of course, the maximum thickness has to be controlled in all these applications.To handle such a variety of design problems, a n
43、umber of design procedures havebeen developed. Several of them are described briefly in this paper, and some examplesare discussed.703Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-SYMBOLSA,A2 Fourier coefficients *.c airfoil chordc airfoil lift coe
44、fficientc, . airfoil lift coefficient at zero angle of attack1,0 - cm airfoil pitching-moment coefficient - (j airfoil pressure coefficient - . M Mach number .t airfoil thickness , -x axial distance with origin at airfoil leading edgea. angle of attack . aideal ideal angle of attack .0 =e(7r) . . .
45、, :6j,62 phase anglese function relating angular coordinates of near-circle and exact-circle airfoiltransformationsq angular coordinate of exact-circle transformation of airfoilt/ function relating radial coordinates of near-circle and exact-circle airfoiltransformations -i/ average value of fy , .
46、. .704Provided by IHSNot for ResaleNo reproduction or networking permitted without license from IHS-,-,-DESIGN OF SUPERCRITICAL AIRFOILS FOR APRESCRIBED PRESSURE DISTRIBUTIONFigure 1 is a schematic outline of a computerized procedure that is intended toprovide the designer with one of his most impor
47、tant tools: a means of obtaining the kindof pressure distribution that he wants (ref. 1). This computer program requires an ini-tial airfoil whose pressure distribution, indicated by a solid line, is known. It thentailors the airfoil to obtain the desired pressure,distribution, indicated by a dashed
48、 line,as nearly as possible within the constraints of the program. A formula based on thestreamline curvature momentum equation relates the prescribed changes in local veloc-ity to corresponding changes in local curvature. The new curvature distribution is usedto reconstitute, by a purely geometric construction, a revised contour This contour isthen adjusted linearly
