Critical hypersonic aerothermodynamic phenomena

Annual Review of Fluid Mechanics

Volumn 38, Issue , 2006, Pages 129-157

  Bertin, John J ^a,b   Cummings, Russell M ^b  

^a Rice University   (United States)

^b UNITED STATES AIR FORCE ACADEMY   (United States)

Author keywords

Boundary layer transition; CFD; Flight testing; Ground testing; Hypersonic

Indexed keywords

BOUNDARY LAYER FLOW; COMPUTATIONAL FLUID DYNAMICS; FLIGHT DYNAMICS; HYPERSONIC FLOW; NUMERICAL METHODS;

BOUNDARY LAYER TRANSITION; FLIGHT TESTING; GROUND TESTING; HYPERSONIC AEROTHERMODYNAMIC PHENOMENA;

HYPERSONIC AERODYNAMICS;

BOUNDARY LAYER FLOW; COMPUTATIONAL FLUID DYNAMICS; FLIGHT DYNAMICS; HYPERSONIC AERODYNAMICS; HYPERSONIC FLOW; NUMERICAL METHODS;

COMPUTATIONAL FLUID DYNAMICS;

EID: 32644433215     PISSN: 00664189     EISSN: None     Source Type: Book Series    
DOI: 10.1146/annurev.fluid.38.050304.092041     Document Type: Review

References (122)

1. θ = 1685. J. Fluid Mech. 420:47-83
2. Anderson A, Matthews RK. 1993. Aerodynamic and aerothermal facilities. I. Hypersonic wind tunnels. In Methodology of Hypersonic Testing Conf. Belgium: Von Karman Inst.
3. Anderson JD. 1989. Hypersonic and High Temperature Gas Dynamics. New York: McGraw-Hill
4. Armstrong JG. 1969. Flight planning and conduct of the X-15A-2 envelope expansion program. Air Force Flight Test Cent. FTC-TD-69-4, Edwards, CA
5. Bekey I, Powell R, Austin R. 1994. NASA studies access to space. Aerosp. Am. 32:38-43
6. Berry SA, Auslender AH, Dilley AD, Calleja JF. 2001a. Hypersonic boundary-layer trip development for Hyper-X. J. Spacecr. Rocket. 38:853-64
7. Berry SA, Horvath TJ, Hollis BR, Thompson RA, Hamilton HH. 2001b. X-33 hypersonic boundary-layer transition. J. Spacecr. Rockets. 38:646-57
8. Bertin JJ. 1994. Hypersonic Aerothermodynamics. Washington, DC: AIAA
9. Bertin JJ, Bouslog SA, Wang KC, Campbell CH. 1996. Recent aerothermodynamic flight measurements during Shuttle Orbiter re-entry. J. Spacecr. Rockets 33:457-62
10. Bertin JJ, Cummings RM. 2003. Fifty years of hypersonics: where we've been, where we're going. Progr. Aerosp. Sci. 39:511-36
11. Bird GA. 1976. Molecular Gas Dynamics. Oxford: Clarendon
12. Bird GA. 1978. Monte Carlo simulation of gas flows. Annu. Rev. Fluid Mech. 10:11-31
13. Bird GA. 1994. Molecular Gas Dynamics and the Direct Simulation of Gas Flows. New York: Oxford Univ. Press
14. Boison JC, Curtiss HA. 1959. An experimental investigation of blunt body stagnation point velocity gradient. ARS J. 29:130-35
15. Buck ML, Benson BR, Sieron TR, Neumann RD. 1963. Aerodynamic and performance analyses of a superorbital re-entry vehicle. In Dynamics of Manned Lifting Planetary Entry, ed. SM Scala, AC Harrison, M Rogers, pp. 376-407. New York: Wiley
16. Buning PG, Wong T-C, Dilley AD, Pao JL. 2001. Computational fluid dynamics prediction of Hyper-X stage separation aerodynamics. J. Spacecr. Rockets. 38:820-27
17. Burcham FW, Nugent J. 1970. Local flow field around a pylon-mounted dummy ramjet engine on the X-15-2 airplane for Mach numbers from 2.0 to 6.7. NASA Tech. Note D-5638
18. Bushnell DM. 1997. Hypersonic flight experimentation - status and shortfalls. Presented at AGARD Interpanel Symp. Future Aerospace Technol. Serv. Alliance, AGARD CP-6000, Paris
19. Cheng HK. 1993. Perspectives on hypersonic viscous flow research. Annu. Rev. Fluid Mech. 25:455-84
20. Cheng HK, Emanuel G. 1995. Perspective on hypersonic nonequilibrium flow. AIAA J. 33:385-400
21. Cockrell CE, Engelund WC, Bittner RD, Jentink TN, Dilley AD, Frendi A. 2001. Integrated aeropropulsive computational fluid dynamics methodology for the Hyper-X flight experiment. J. Spacecr. Rockets 38:836-43
22. Columbia Accid. Investig. Board. 2003. Accident Analysis. pp. 49-84. Vol. 1, Ch. 3. Govt. Printing Office
23. Cooke JC. 1961. An axially symmetric analogue for general three-dimensional boundary layers. Aeronaut. Res. Counc. TR RM 3200. Br. Minist. Aviat., June
24. Cornette ES. 1966. Forebody temperatures and calorimeter heating rates measured during project Fire II reentry at 11.35 kilometers per second. NASA Tech. Mem. X-1035
25. Detra RW, Kemp NH, Riddell FR. 1957. Addendum to heat transfer to satellite vehicles reentering the atmosphere. Jet Propuls. 27:1256-57
26. Dorrance WH. 1962. Viscous Hypersonic Flow. New York: McGraw-Hill
27. Eckert ERG. 1955. Engineering relations for friction and heat transfer to surfaces in high velocity flow. J. Aeronaut. Sci. 22:585-87
28. Edney BE. 1968a. Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Flygtek. Foersoeksanstalten (FFA) Rep. 115
29. Edney BE. 1968b. Effects of shock impingement on the heat transfer around blunt boies. AIAA J. 6:15-21
30. Edwards TA. 1992. Fluid/chemistry modeling for hypersonic flight analysis. Comput. Math. Appl. 24:25-36
31. Engelund WC. 2001. Hyper-X aerodynamics: the X-43A airframe-integrated Scramjet propulsion flight-test experiments. J. Spacecr. Rockets 38:801-2
32. Engelund WC, Holland SD, Cockrell CE, Bittner RD. 2001. Aerodynamic database development for the Hyper-X airframe-integrated scramjet propulsion experiments. J. Spacecr. Rockets 38:803-10
33. Fasel H, Thumm A, Bestel H. 1993. Direct numerical simulation of transition in supersonic boundary layer: oblique breakdown. In Transitional and Turbulent Compressible Flows, ed. LD Kral, TA Zang, pp. 77-92. New York: ASME
34. Favre A. 1965. Equations des gaz turbulents compressibles. J. Mec. 4:361-90
35. Fay JA, Riddell FR. 1958. Theory of stagnation point heat transfer in dissociated air. J. Aeronaut. Sci. 25:73-85, 121
36. Forsythe JR, Hoffmann KA, Cummings RM, Squires KD. 2002. Detached-eddy simulation with compressibility corrections applied to a supersonic axisymmetric base flow. J. Fluid. Eng. 124:911-23
37. Fujii K, Watanabe S, Kurotaki T, Shirozu M. 2001. Aerodynamic heating measurements on nose and elevon of hypersonic flight experiment vehicle. J. Spacecr. Rockets 38:8-14
38. Fujimoto K, Fujii K, Tsuboi N. 2003. CFD prediction of the aerodynamic characteristic of capsule-like configurations for the future SSTO development. Presented at AIAA Aerosp. Sci. Meet., 41st, AIAA Pap. 03-0912, Reno, NV
39. Glass DE, Holden MS, Wieting AR. 1989. Effect of leading edge sweep on shock/shock interference at Mach 8. Presented at AIAA Aerosp. Sci. Meet., 27th, AIAA Pap. 89-0271, Reno, NV
40. Gnoffo PA, Weilmuenster KJ, Hamilton HH, Olynick DR, Venkatapathy E. 1999. Computational aerothermodynamic design issues for hypersonic vehicles. J. Spacecr. Rockets 36:21-43
41. Godunov SK. 1959. Finite-difference method for numerical computation of discontinuous solutions of the equations of fluid dynamics. Mat. Sb. 47:271-306
42. Haney JW. 1983. Orbiter entry heating lessons learned from development flight test program. NASA CP 2283, pp. 719-51
43. Harten A.1983. High resolution schemes for hyperbolic conservation laws. J. Comput. Phys. 49:357-93
44. Hayes WD, Probstein RF. 1959. Hypersonic Flow Theory. New York: Academic
45. Hildebrand FB. 1957. Advanced Calculus for Engineers. Englewood Cliffs, NJ: Prentice-Hall
46. Hirschel EH. 1991. Viscous effects. Proc. Space Course, pp. 12:1-35. MBB-FE202/S/PUB/441. Aachen, Germany
47. Hodge JK, Audley DR. 1983. Aerothermodynamic parameter estimation from shuttle thermocouple data during transient flight test maneuvers. J. Spacecr. Rockets 23:453-60
48. Holden M, Chadwick K, Kolly J. 1995. Hypervelocity studies in the LENS facility. Presented at Int. Aerosp. Planes Hyper. Tech. Conf., 6th, AIAA Pap. 95-6040, Chattanooga, TN
49. Holland SD, Woods WC, Engelund WC. 2001. Hyper-X research vehicle experimental aerodynamics test program overview. J. Spacecr. Rockets 38:828-35
50. Hollis BR, Horvath TJ, Berry SA, Hamilton HH, Thompson RA, Alter SJ. 2001a. X-33 computational aeroheating predictions and comparisons with experimental data. J. Spacecr. Rockets 38:658-69
51. Hollis BR, Thompson RA, Murphy KJ, Nowak RJ, Riley CJ, et al. 2001b. X-33 aerodynamic computations and comparisons with wind-tunnel data. J. Spacecr. Rockets 38:684-91
52. Horvath TJ, Berry SA, Hollis BR, Liechty DS, Hamilton HH, Merski NR. 2001. X-33 experimental aeroheating at Mach 6 using phosphor thermography. J. Spacecr. Rockets 38:634-45
53. Huebner LD, Rock KE, Ruf EG, Witte DW, Andrews EH. 2001. Hyper-X flight engine ground testing for flight risk reduction. J. Spacecr. Rockets 38:844-52
54. Ivanov MS, Gimelshein SF. 1998. Computational hypersonic rarefied flows. Annu. Rev. Fluid Mech. 30:469-505
55. Jones WP, Launder BE. 1973. The calculation of low-Reynolds-number phenomena with a two-equation model of turbulence. Int. J. Heat Mass Trans. 16:1119-30
56. Kim KH, Kim C, Rho OH. 2001a. Methods for the accurate computations of hypersonic flows: AUSMPW+scheme. J. Comput. Phys. 174:38-80
57. Kim KH, Kim C, Rho OH. 2001b. Methods for the accurate computations of hypersonic flows: shock-aligned grid technique. J. Comput. Phys. 174:81-119
58. Kogan MN. 1973. Molecular gas dynamics. Annu. Rev. Fluid Mech. 5:383-404
59. Lax PD, Wendroff B. 1960. Systems of conservation laws. Commun. Pure Appl. Math. 13:217-37
60. LeBeau GJ. 1999. A parallel implementation of the direct simulation Monte Carlo method. Comput. Methods Appl. Mech. Eng. 174:319-37
61. LeBeau GJ, Lumpkin FE. 2001. Application highlights of the DSMC analysis code (DAC) software for simulating rarefied flows. Comput. Methods Appl. Mech. Eng. 191:595-609
62. Lee DB, Goodrich WD. 1972. The aerothermodynamic environment of the Apollo command module during suborbital entry. NASA Tech. Note D-6792
63. Lees L. 1955. Hypersonic flow. Proc. 5th Int. Aero. Conf., Los Angeles, pp. 241-75. New York. Inst. Aeronaut. Sci.
64. Lees L. 1956. Laminar heat transfer over blunt-nosed bodies at hypersonic flight speeds. Jet Propuls. 26:259-69, 274
65. Lele SK. 1992. Compact finite difference schemes with spectral-like resolution. J. Comput. Phys. 103:16-42
66. Longo JMA, Orlowski M, Brück S. 2000. Consideration on CFD modeling for the design of re-entry vehicles. Aerosp. Sci. Technol. 4:337-45
67. Longo JMA. 2003. Aerothermodynamics - a critical review at DLR. Aerosp. Sci. Technol. 7:429-38
68. MacCormack RW. 1969. The effect of viscosity in hypervelocity impact cratering. AIAA Pap. 69-354
69. Martin MP. 2004. DNS of hypersonic turbulent boundary layers. Presented at AIAA Fluid Dyn. Conf., 34th, AIAA Pap. 2004-2337, Portland, OR
70. Matthews RK, Nutt KW, Wannenwetsch GD, Kidd CT, Boudreau AH. 1984. Developments in aerothermal test techniques at the AEDC supersonic-hypersonic wind tunnels. Presented at AIAA Therm. Conf., 20th, AIAA Pap. 84-1803, Williamsburg, VA
71. Maus JR, Griffith BJ, Szema KY, Best JT. 1984. Hypersonic Mach number and real-gas effects on space shuttle aerodynamics. J. Spacecr. Rockets 21:136-41
72. Mehta UB. 1993. Aerospace plane design challenge: credible computations. J. Aircr. 30:519-25
73. Men'shov IS, Nakamura Y. 2000. Numerical simulations and experimental comparison for high-speed nonequilibrium. air flows. Fluid Dyn. Res. 27:305-34
74. Menter FR. 1994. Two-equation eddy-viscosity turbulence models for engineering applications. AIAA J. 32:1598-605
75. Moin P. 2002. Advances in large eddy simulation methodology for complex flows. Int. J. Heat Fluid Flow 23:710-20
76. Moretti G. 1974. On the matter of shock fitting. Lect. Notes Phys. 35:287-92
77. Mulder WA, Van Leer B. 1985. Experiments with implicit upwind methods for the Euler equations. J. Comput. Phys. 59:232-46
78. Muntz EP. 1989. Rarefied gas dynamics. Annu. Rev. Fluid Mech. 21:387-417
79. Murphy KJ, Nowak RJ, Thompson RA, Hollis BR, Prabhu R. 2001. X-33 hypersonic aerodynamic characteristics. J. Spacecr. Rockets 38:670-83
80. Neumann RD. 1988. Missions and requirements. Presented at Spec. Course Aerothermodyn. Hypersonic Veh., AGARD Rep. 761, Neuilly sur Seine, Fr.
81. Neumann RD. 1989. Defining aerothermodynamic methodology. In Hypersonics. Volume I: Defining the Hypersonic Environment, ed. JJ Bertin, R Glowinski, J Periaux. pp. 125-204. Boston: Birkhaeuser
82. Nompelis I, Candler GV, Holden MS. 2003. Effect of vibrational nonequilibrium on hypersonic double-cone experiments. AIAA J. 41:2162-69
83. Osher S, Solomon F. 1982. Upwind difference schemes for hyperbolic systems of conservation laws. Math. Comput. 38:339-74
84. Papadopoulos P, Venkatapathy E, Prabhu D, Loomis MP, Olynick D. 1999. Current grid-generation strategies and future requirements in hypersonic vehicle design, analysis, and testing. Appl. Math. Model 23:705-35
85. Park C. 1989. Assessment of two-temperature kinetic model for ionizing flow. J. Thermophys. Heat Trans. 3:233-44
86. Park C. 1990. Nonequilibrium Hypersonic Aerothermodynamic. New York: Wiley-Intersci.
87. Park C, Yoon S. 1991. Fully coupled implicit method for thermochemical nonequilibrium air at suborbital flight speeds. J. Spacecr. Rockets 28:31-39
88. Pirzadeh S. 2001. Vortical flow prediction using an adaptive unstructured grid method. Presented at NATO Res. Technol. Organ. Meet., Loen, Nor.
89. Reubush DE, Omar ME. 1989. Pressure and heat transfer investigation of a modified NASP baseline configuration at M = 6. Presented at AIAA Acrosp. Sci. Meet., 27th, AIAA Pap. 89-0246, Reno, NV
90. Reynolds O. 1895. On the dynamical theory of incompressible viscous fluids and the determination of the criterion. Philos. Trans. R. Soc. Ser. A 186:123-64
91. Roe PL. 1986. Characteristic-based schemes for the Euler equations. Annu. Rev. Fluid Mech. 18:337-65
92. Romere PO, Young JC. 1983. Space shuttle entry longitudinal aerodynamic comparisons of flight 2 with preflight predictions. J. Spacecr. Rockets 20:518-23
93. Sarma GSR. 2000. Physico-chemical modeling in hypersonic flow simulation. Prog. Aerosp. Sci. 36:281-349
94. Schaaf SA. 1963. Mechanics of rarefied gases. In Handbuch der Physik, Strömungsmechnik II, ed. S Flügge. pp. 591-624. Berlin: Springer-Verlag
95. Schneider SP. 2004. Hypersonic laminar-turbulcnt transition on circular cones and scramjet forebodies. Prog. Aerosp. Sci. 40:1-50
96. Schneider SP. 1999. Flight data for boundary-layer transition at hypersonic and supersonic speeds. J. Spacecr. Rockets 36:8-20
97. Scott CD, Ried RC, Maraia RJ, Li CP, Derry SM. 1985. An AOTV aeroheating and thermal protection study. In Thermal Design of Aeroazisted Orbital Transfer Vehicles, ed. HE Nelson, 96:198-229. New York: AIAA
98. Sherman FS. 1969. The transition from continuum to molecular flow. Annu. Rev. Fluid Mech. 1:317-40
99. Sietzen F. 2005. From Mercury to CEV: space capsules reemerge. Aerosp. Am. 43(2):26-33
100. Spalart PR, Allmaras SR. 1992. A one-equation turbulence model for aerodynamic flows. Pesented at AIAA Aerosp. Sci. Meet., 30th, AIAA Pap. 92-0439, Reno, NV
101. Spalart PR, Jou W-H, Strelets M, Allmaras SR. 1997. Comments on the feasibility of LES for wings, and on a hybrid RANS/LES approach. In Advances in DNS/LES. Columbus: Greydon
102. Steger JL, Warming RF. 1981. Flux vector splitting of the inviscid gasdynamic equations with application to finite difference methods. J. Comput. Phys. 40:263-93
103. Stollery JL. 1987. Some aspects of shock-wave boundary-layer interaction relevant to intake flows. In Aerodynamics of Hypersonic Lifting Vehicles, AGARD CP 428
104. Stoney WE Jr. 1958. Aerodynamic heating on blunt-nose shapes at Mach numbers up to 14. In NACA Conf. High Speed Aerodyn. Ames Aeronaut. Lab., Moffett Field, CA. NACA RM L58E05a
105. Surber TE, Olsen DC. 1978. Space shuttle orbiter aerodynamic development. J. Spacecr. Rockets 15:40-47
106. Sutton K, Graves RA. 1971. A general stagnation-point convective heating equation for arbitrary gas mixtures. NASA Tech. Rep. R-376
107. Suzen YB, Hoffmann KA. 1998. Investigation of supersonic jet exhaust flows by one- and two-equation turbulence models. Presented at AIAA Aerosp. Sci. Meet., 36th, AIAA Pap. 98-0322, Reno, NV
108. Throckmorton DA. 1992. Shuttle entry aerothermodynamic flight research: the Orbiter experiments progrom. Presented at AIAA Aerosp. Ground Test. Conf., 17th, AIAA Pap. 92-3987, Nashville, TN
109. Tirsky GA. 1993. Up-to-date gasdynamic models of hypersonic aerodynamics and heat transfer with real gas properties. Annu. Rev. Fluid Mech. 25:151-81
110. Trimmer LL, Cary AM, Voisinet RL. 1986. The optimum hypersonic wind tunnel. Presented at Aero. Test. Conf., 14th, AIAA Pap. 86-0739, West Palm Beach, FL
111. Van Leer B. 1979. Towards the ultimate conservative difference scheme. J. Comput. Phys. 32:101-36
112. Weiland C, Longo J, Gülhan A, Decker K. 2004. Aerothermodynamics for reusable launch systems. Aerosp. Sci. Tech. 8:101-10
113. Westkaemper JC. 1968. Turbulent boundary-layer separation ahead of cylinders. AIAA J. 6:1352-55
114. Weston KC, Fitzkee AL. 1963. Afterbody heat transfer measurements obtained during reentry of the spacecraft of the Mercury-Atlas 5 mission. NASA Tech. Mem. X-564
115. Weston KC, Swanson JE. 1961. A compilation of wind-tunnel heat-transfer measurements on the afterbody of the Project Mercury capsule reentry configuration. NASA Tech. Mem. X-495
116. Whitnah AM, Hillje ER. 1984. Space shuttle wind tunnel testing program summary. NASA Ref. Publ. 1125
117. Wilcox DC. 1988. Reassessment of the scale determining equation for advanced turbulence models. AIAA J. 26:1299-310
118. Williamson WE. 1992. Hypersonic flight testing. Presented at AIAA Aerosp. Ground Test. Conf., 17th, AIAA Pap. 92-3989, Nashville, TN
119. Woods WC, Arrington JP, Hamilton HH. 1983. A review of preflight estimates of real-gas effects on space shuttle aerodynamic characteristics. In Shuttle Performance: Lessons Learned. NASA Conf. Publ. 2283
120. Woods WC, Holland SD, DiFulvio M. 2001. Hyper-X stage separation wind-tunnel test program. J. Spacecr. Rockets 38:881-19
121. Wright RL, Zoby EV. 1977. Flight boundary layer transition measurements on a slender cone at Mach 20. Presented at AIAA Plasma Fluid Dyn. Conf., 10th, AIAA Pap. 77-719, Albuquerque, NM
122. Yen SM. 1984. Numerical solution of the nonlinear Boltzmann equation for nonequilibrium gas flow problems. Annu. Rev. Fluid Mech. 16:67-97