Perspectives on hypersonic viscous flow research

Annual Review of Fluid Mechanics

Volumn 25, Issue 1, 1993, Pages 455-484

  Cheng, H K ^a  

^a UNIVERSITY OF SOUTHERN CALIFORNIA   (United States)

Author keywords

Hypersonic boundary layer instability; Hypersonic flight; Hypersonic flow computation; Theoretical gas dynamics; Viscous interaction

Indexed keywords

EID: 0010864959     PISSN: 00664189     EISSN: None     Source Type: Book Series    
DOI: 10.1146/annurev.fl.25.010193.002323     Document Type: Review

References (154)

1. Anderson, D. A., Tannehill, J. C., Pletcher, R. H. 1984. Computational Fluid Mechanics and Heat Transfer. Hemisphere
2. Anderson, J. D. Jr. 1989. Hypersonic and High Temperature Gas Dynamics. New York: McGraw-Hill
3. Anderson, J. D., Chang, J., McLaughlin, T. A. 1992. Hypersonic waveriders: effects of chemically reacting flow and viscous interaction. AIAA Pap. 92-0302
4. Anderson, J. D., Ferguson, F., Lewis, M. J. 1991. Hypersonic waveriders for high altitude applications. AIAA Pap. 91-0530
5. Anderson, J. D., Lewis, M. J., Corda, S., Blankson, I. M., eds. 1990. Proc. 1st Int. Hypersonic Waverider Symp., Univ. Maryland, Oct. 17-19, 1990; to appear as AIAA Prog. Astronaut. Aeronaut. Ser.
6. Anderson, J. D., Lewis, M. J., Corda, S., Blankson, I. M., eds. 1990. Proc. 1st Int. Hypersonic Waverider Symp., Univ. Maryland, Oct. 17-19, 1990; to appear as AIAA Prog. Astronaut. Aeronaut. Ser.
7. Balsa, T. F., Goldstein, M. E. 1990. On the instabilities of supersonic mixing layers: a high Mach number asymptotic theory. J. Fluid Mech. 216: 585-611
8. Beckwith, I. E., Holley, B. B. 1981. Görtler vortices and transition in wall boundary layers of two Mach 5 nozzles. NASA TP-1869
9. Billig, F. S. 1992. Research on supersonic combustion. AIAA Pap. 92-0001
10. Blackaby, N. D., Cowley, S. J., Hall, P. 1992. On the instability of hypersonic flow past a flat plate. J. Fluid Mech. In press
11. Blottner, F. G. 1990. Accurate Navier-Stokes calculation for hypersonic flow over a spherical nosetip. J. Spacecr. Rockets 27: 113-22
12. Bowcutt, K. G., Anderson, J. D., Capriotti, D. 1987. Viscous optimized hypersonic waveriders, AIAA Pap. 87-0272
13. Brown, S. N., Cheng, H. K., Lee, C. J. 1990. Inviscid-viscous interaction on triple-deck scales in a hypersonic flow with strong wall cooling. J. Fluid Mech. 220: 309-37
14. Brown, S. N., Khorrami, A. F., Neish, A., Smith, F. T. 1991. On hypersonic boundary layer interaction and transition. Philos. Trans. R. Soc. London Ser. A 335: 139-52
15. Brown, S. N., Stewartson, K. S. 1975. A nonuniqueness of the hypersonic boundary layer. Quart. J. Mech. Appl. Math. 28: 75-90
16. Brown, S. N., Stewartson, K. S., Williams, P. G. 1975. Hypersonic self-induced separation. Phys. Fluids 18: 633-39
17. Burggraf, O. R., Rizzetta, D., Werle, M. J., Vasta, V. N. 1979. Effect of Reynolds number on laminar separation on a supersonic stream. AIAA J. 17: 336-43
18. Burnett, D. 1936. The distribution of molecular velocities and the mean motion in a nonuniform gas. Proc. London Math. Soc. Ser. 240(3): 382-430
19. Burns, B. R. A. 1989. Aerodynamic design challenge of a single stage to orbit, reusable launch vehicle. Proc. Int. Conf. Hypersonic Aerodynamics. Univ. Manchester, UK, Pap. No. 1
20. Bush, W. B. 1966. Hypersonic strong-interaction similarity solutions for flow past a flat plate. J. Fluid Mech. 25: 51-64
21. Bush, W. B., Cross, A. K. 1967. Hypersonic weak-interaction similarity solutions for flow past a flat plate. J. Fluid Mech. 29: 349-59
22. Butta, B. A., Song, D. J., Lewis, C. H. 1990. Nonequilibrium viscous hypersonic flows over ablating Teflon surfaces. J. Spacecr. Rockets 27: 194-204
23. Cebeci, T., Bradshaw, P. 1988. Physical and Computational Aspects of Convective Heat Transfer. Berlin: Springer-Verlag
24. Chapman, D. R. 1992. A perspective on aerospace CFD. Aerosp. Am. Jan. 16-59
25. Cheng, H. K. 1963. The blunt-body problem in hypersonic flow at low Reynolds number. Cornell Aero. Lab. Rep. AF-1285-A-10
26. Cheng, H. K. 1966. Viscous hypersonic blunt-body problem and the Newtonian theory. In Fundamental Phenomena in Hypersonic Flow, ed. G. J. Hall, pp. 91-132. Ithaca: Cornell Univ. Press
27. Cheng, H. K. 1990. Book review: Hypersonic and High-Temperature Gas Dynamics by J. D. Anderson, Jr. AIAA J. 28: 766-68
28. Cheng, H. K. 1992. Perspectives o1n hyper-sonic viscous and nonequilibrium hypersonic flow research. Univ. So. Calif. Dept. Aerospace Eng. Rep. USCAE 151
29. Cheng, H. K., Lee, C. J., Wong, E. Y., Yang, H. T. 1989. Hypersonic slip flows and issues on extending continuum model beyond the Navier-Stokes level. AIAA Pap. 89-1663
30. Cheng, H. K., Wong, E. Y., Dogra, V. K. 1991. A shock-layer theory based on thirteen-moment equations and DSMC calculations of rarefied hypersonic flows. AIAA Pap. 91-0783
31. Cheng, S. I. 1989. Hypersonic combustion. Proc. Energy Combust. Sci. 15: 183-202
32. Cheung, S., Cheer, A., Hafez, M., Flores, J. 1991. Convergence acceleration of viscous and inviscid hypersonic flow calculations. AIAA J. 29: 1214-23
33. Corda, S., Anderson, J. D. Jr. 1988. Viscous optimized hypersonic wavenders designed from axisymmetric flow fields. AIAA Pap. 88-0369
34. Cowley, S. J., Hall, P. 1990. The instability of hypersonic flow past a wedge. J. Fluid Mech. 214: 17-42
35. Cox, R. N., Crabtree, L. F. 1965. Elements of Hypersonic Aerodynamics. Cambridge: Cambridge Univ. Press
36. Davis, R. T. 1970. Numerical solution of the hypersonic viscous shock-layer equations. AIAA J. 8: 843-51
37. Demetriades, A. 1978. New experiments on hypersonic boundary layer stability including wall temperature effects. AIAA Pap. 74-535 (1974)
38. Edney, B. 1968. Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Aeronaut. Res. Inst. Sweden, Stockholm, Rep. 115; also AIAA J. 6: 15-21
39. Edney, B. 1968. Anomalous heat transfer and pressure distributions on blunt bodies at hypersonic speeds in the presence of an impinging shock. Aeronaut. Res. Inst. Sweden, Stockholm, Rep. 115; also AIAA J. 6: 15-21
40. Edwards, T. A., Flores, J. 1990. Computational fluid dynamics nose-to-tail capability: hypersonic unsteady Navier-Stokes code validation. J. Spacecr. Rockets 27: 123-30
41. Eggers, A. J., Ashley, H., Springer, G. 1990. Waverider configuration from the 1950's to the 1990's. Proc. 1st Int. Hypersonic Waverider Symp., Univ. Maryland, Oct. 17-19, 1990
42. Gajjar, J., Smith, F. T. 1983. On hypersonic self-induced separation: hydraulic jumps and boundary layers with algebraic growth. Mathematika 30: 77-93
43. Glass, C. E., Weiting, A. R., Holden, M. S. 1989. Swept shock-on-lip - A comparison of analytical and experimental results. NASA TN 1085
44. Gnoffo, P. A. 1990. Code calibration program in support of the aeroassisted flight experiment. J. Spacecr. Rockets 27: 131-42
45. Goldstein, M. E., Wundrow, D. W. 1990. Spatial evolution of nonlinear acoustic mode instabilities on hypersonic boundary layers. J. Fluid Mech. 219: 585-607
46. Greendyke, R. B., Gnoffo, P. A., Lawrence, R. W. 1992. Electron number density profile for the aeroassist flight experiment. AIAA Pap. 92-0804
47. Gupta, R. N., Lee, K. P., Zobby, E. V. 1992. Enhancements to viscous-shock-layer technique. AIAA Pap. 92-2897
48. Hamilton, H. H., Gupta, R. N., Jones, J. J. 1991. Flight stagnation-point heating calculations of AFE vehicle. J. Spacecr. Rocket 28: 125-28
49. Harten, A. 1983. High resolution schemes for hypersonic conservation laws. J. Comput. Phys. 49: 357-93
50. Hayes, W. D., Probstein, R. F. 1959. Hypersonic Flow Theory. New York: Academic
51. Herbert, Th. 1988. Secondary instability of boundary layers. Annu. Rev. Fluid Mech. 20: 487-526
52. Hoffman, K. A. 1989. Computational Fluid Dynamics for Engineers. Austin, Tex.: Eng. Ed. Sys.
53. Holden, M., Moselle, J. R. 1969. Theoretical and experiment studies of the shock waveboundary layer interaction on compression surfaces in hypersonic flow. CALSPAN Rep. AF-2410-A-1
54. Holden, M., Wieting, A. R., Moselle, J., Glass, C. 1988. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow. AIAA Pap. 88-0477; also NASP TN 1085 (1989)
55. Holden, M., Wieting, A. R., Moselle, J., Glass, C. 1988. Studies of aerothermal loads generated in regions of shock/shock interaction in hypersonic flow. AIAA Pap. 88-0477; also NASP TN 1085 (1989)
56. Hornung, H. 1988. Lanchester memorial lecture - experimental real-gas hypersonics. Aeronaut. J. 92: 379-89; also Z. Flugwiss. Weltraumf 12: 293
57. Hornung, H. 1988. Lanchester memorial lecture - experimental real-gas hypersonics. Aeronaut. J. 92: 379-89; also Z. Flugwiss. Weltraumf 12: 293
58. Hornung, H., Sturtevant, B., Bélanger, J., Sanderson, S., Brouillette, M., Jenkine, M. 1992. Performance data of the new free-piston shock tunnel T5 at GALCIT. Cal. Inst. Tech. Grad. Aero. Lab. Memo.
59. Hung, C. M., Barth, T. J. 1990. Computation of hypersonic flow through a narrow expansion slot. AIAA J. 28: 229-35
60. Hung, C. M., MacCormack, R. W. 1975. Numerical solutions of supersonic and hypersonic laminar flows over a twodimensional compression corner. AIAA Pap. 75-2
61. Ito, T., Akimoto, H., Miyaba, H., Kano, Y., Suzuki, N., Sasaki, H. 1990. Concept and technology development for HOPE spaceplane. AIAA Pap. 90-5223
62. Kang, S. H., Kunc, J. A. 1991. Viscosity of high-temperature iodine. Phys. Rev. A 44: 3596-3604
63. Kendall, J. M. 1975. Wind tunnel experiments relating to supersonic and hypersonic boundary layer transition. AIAA J. 13: 240-99; see also Aerosp. Corp. Rep. BSD-TR-67-213,2 (1967)
64. Kendall, J. M. 1975. Wind tunnel experiments relating to supersonic and hypersonic boundary layer transition. AIAA J. 13: 240-99; see also Aerosp. Corp. Rep. BSD-TR-67-213,2 (1967)
65. Koelle, D. 1990. Sänger advanced space transportation system - progress report 1990. AIAA Pap. 90-5200
66. Krawczyk, W., Harris, T., Rajendran, N., Carlson, D. 1989. Progress in the development of PNS technology for external and internal flows. AIAA Pap. 89-1828
67. Küchemann, D. 1978. The Aerodynamic Design of Aircraft. Oxford: Pergamon
68. Lee, R. S., Cheng, H. K. 1969. On the outeredge problem of a hypersonic boundary layer. J. Fluid Mech. 38: 161-79
69. Lee, S. H., Deiwert, G. S. 1990. Flux-vector splitting calculation of nonequilibrium hydrogen-air reactions. J. Spacecr. Rockets 27: 167-74
70. Lees, L., Lin, C. C. 1946. Investigation of the stability of the laminar boundary layers in a compressible fluid. NACA TN 1115
71. Lesieur, M. 1990. Turbulence in Fluids. Dordrecht: Kluwer
72. Lighthill, M. J. 1953. On boundary layer and upstream influence II. Supersonic flow without separation. Proc. R. Soc. London Ser. A 217: 478-507
73. Liu, F., Jameson, A. 1992. Multi-grid NavierStokes calculations for 3-D cascades. AIAA Pap. 92-0190
74. Lozino-Lozinsky, Ye. G., Neiland, V. Ya. 1989. The convergence of the Buran orbiter flight test and preflight study results and the choice of a strategy to develop a second-generation orbiter. AIAA Pap. 89-5019
75. MacCormack, R. W. 1982. A numerical method for solving the equations of compressible viscous flow. AIAA J. 20: 1275-81
76. MacCormack, R. W. 1990. Solution of the Navier-Stokes equations in three dimensions. AIAA Pap. 90-1520
77. MacCormack, R. W., Baldwin, B. S. 1975. A numerical method for solving the NavierStokes equations with application to shockboundary layer interaction. AIAA Pap. 75-1
78. MacCormack, R. W., Candler, G. V. 1989. The solution of the Navier-Stokes equations using Gauss-Seidel line relaxation. Comput. Fluids 17: 135-50
79. Mack, L. M. 1984. Boundary layer linear stability theory. AGARD Rep. 709; also see AIAA J. 13: 278-89 (1975)
80. Mack, L. M. 1984. Boundary layer linear stability theory. AGARD Rep. 709; also see AIAA J. 13: 278-89 (1975)
81. Mack, L. M. 1987a. Review of linear compressible stability theory. In Stability of Time Dependent and Spatially Varying Flow, ed. D. L. Dwoyer, M. Y. Hussaini, pp. 164-87. New York: Springer-Verlag
82. Mack, L. M. 1987b. Stability of axisymmetric boundary layer on sharp cones at hypersonic Mach number. AIAA Pap. 87-1413
83. Malik, M. R., Hussaini, M. Y. 1990. Numerical simulation of interactions between Görtler vortices and Tollmien-Schlichting waves. J. Fluid Mech. 210: 183-99
84. Malik, M. R., Zang, T., Bushnell, D. 1990. Boundary layer transition in hypersonic flows. AIAA Pap. 90-5232
85. Mehta, U. B. 1990. Computational requirements for hypersonic performance estimates. AIAA J. 27: 103-12
86. Mikhailov, V. V., Neiland, V. Ya., Sychev, V. V. 1971. The theory of viscous hypersonic flow. Annu. Rev. Fluid Mech. 3: 371-96
87. Moin, P. 1992. The computation of turbulence. Aerosp. Am. Jan: 42-46
88. Moore, F. K. 1964. Hypersonic boundary layer theory. In Theory of Laminar Flow, ed. F. K. Moore, Sec. E: 439-527. Princeton: Princeton Univ. Press
89. Moss, J. N. 1976. Radiative shock layer solutions with coupled ablation injection. AIAA J. 14: 1311-17
90. Moss, J. N., Bird, G. A. 1985. Direct simulation of transitional flow for hypersonic re-entry conditions. Progr. Astro. Aeronaut. 96: 113-39
91. Moss, J. N., Cuda, V., Simmonds, A. L. 1987. Nonequilibrium effects for hypersonic transitional flows. AIAA Pap. 87-0404
92. Ng, L., Erlebacher, G., Zang, T. A., Pruett, D. 1990. Compressible secondary instability theory - parametric studies and prospects for predictive tool. 8th NASP Symp., Pap. no. 23
93. Neiland, V. Ya. 1970. Propagation of perturbation upstream with interaction between a hypersonic flow and a boundary layer. Akad. Nauk. SSSR 3: 19
94. Nonweiler, T. R. F. 1963. Delta wings of shapes amenable to exact shock-wave theory. J. R. Aeronaut. Soc. 67: 39
95. Nonweiler, T. R. F. 1990. The waverider wings in retrospect and prospect. Proc. 1st Int. Waverider Symp., Univ. Maryland, Oct. 17-19, 1990
96. Nonweiler, T. R. F., Wang, H. Y., Aggarwall, S. R. 1971. The role of heat conduction in leading edge heating. Ing. Arch. 40: 107; also see Aero. Res. Council C. D. 1126 (1970)
97. Nonweiler, T. R. F., Wang, H. Y., Aggarwall, S. R. 1971. The role of heat conduction in leading edge heating. Ing. Arch. 40: 107; also see Aero. Res. Council C. D. 1126 (1970)
98. Park, C. 1990. Nonequilibrium Hypersonic Aerothermodynamics. New York: Wiley
99. Parkinson, R., Conchie, P. 1990. HOTOL. AIAA Pap. 90-5201
100. Pham-Van-Diep, G. C., Muntz, E. P., Weaver, D., Dewitt, T. G., Bradley, M. K., et al. 1992. An iodine hypersonic wind tunnel for study of nonequilibrium reacting flows. AIAA Pap. 92-0566
101. Potter, L. J. 1988. Procedure for estimating aerodynamics for 3-D bodies in transitional flow. Prog. Aeronaut. Astronaut. 118
102. Potter, L. J., Whitfield, J. D. 1965. Boundary layer transition under hypersonic conditions. AGARDograph 97, pb. 3: 1-61
103. Pulliam, T. H., Steger, J. L. 1980. Implicit finite-difference simulations of threedimensional compressible flow. AIAA J. 18: 159-67
104. Reshotko, E. 1976. Boundary-layer stability and transition. Annu. Rev. Fluid Mech. 8: 311-50
105. Reynolds, W. C. 1976. Computation of turbulent flows. Annu. Rev. Fluid Mech. 8: 183-208
106. Rizzetta, D. P., Burggaf, O. R., Jenson, R. 1978. Triple-deck solution for viscous supersonic and hypersonic flow past corners. J. Fluid Mech. 89: 535
107. Roe, P. L. 1986. Characteristic-based schemes for the Euler equations. Annu. Rev. Fluid Mech. 18: 337-65
108. Rudy, D. H., Thomas, J. L., Kumar, A., Gnoffo, P. A., Chakravathy, S. R. 1991. Computation of laminar hypersonic compression-corner flows. AIAA J. 29: 1108-13
109. Ryan, J. S., Flores, J., Chow, C. Y. 1990. Development and validation of a Navier-Stokes code for hypersonic external flow. J. Spacecr. Rockets 27: 160-66
110. Sanzero, G. 1990. AIAA Pap. 90-5264
111. Seddougui, T. R. F., Wang, H. Y., Aggarwal, S. R. 1991. Surface-cooling effects on compressible boundary-layer instability, and on upstream influence. Eur. J. Mech. B/Fluids 10: 117-45
112. Shang, J. S., Scherr, S. J. 1986. Navier-Stokes solution for a complete re-entry configuration. J. Aircr. 23: 881-88
113. Simen, M., Dallmann, U. 1992. On instability of hypersonic flow past a pointed cone - comparison of theoretical and experimental results at Mach 8, AGARD Symp. Theor, Exp. Methods Hypersonic Flows, Torino, Italy, May 4-7, 1992
114. Smith, F. T. 1982. On the high Reynolds number theory of laminar flow. IMA J. Appl. Math. 82: 207-81
115. Smith, F. T. 1986. Steady and unsteady boundary-layer separation. Annu. Rev. Fluid Mech. 18: 197-220
116. Smith, F. T. 1989. On first-mode instability in subsonic, supersonic and hypersonic boundary layers. J. Fluid Mech. 198: 127-53
117. Smith, F. T., Brown, S. N. 1990. The inviscid instability of a Blasius boundary layer at large values of the Mach number. J. Fluid Mech. 219:499-518
118. Spall, R. E., Malik, M. R. 1989. Görtler vortices in supersonic and hypersonic boundary layers. Phys. Fluid A 1: 1822-35
119. Steger, J. L., Warming, R. F. 1981. Flux vector splitting of the inviscid gasdynamic equations with application to finitedifference methods. J. Comput. Phys. 40: 263-93; see also NASA TM D-78605
120. Steger, J. L., Warming, R. F. 1981. Flux vector splitting of the inviscid gasdynamic equations with application to finitedifference methods. J. Comput. Phys. 40: 263-93; see also NASA TM D-78605
121. Stetson, K. F. 1988. On nonlinear aspects of hypersonic boundary-layer stability. AIAA J. 26: 883-85
122. Stetson, K. F., Kimmel, R. L. 1992. On hypersonic boundary-layer stability. AIAA Pap. 92-0737
123. Stewartson, K. S. 1955. On motion of a flat plate at high speed in a viscous compressible fluid: part II, steady motion. J. Aeronaut. Sci. 22: 303-9
124. Stewartson, K. S. 1974. Multistructure boundary layers on flat plate and related bodies. Adv. Appl. Mech. 14: 146-239
125. Stewartson, K. S. 1981. D'Alembert's paradox. SIAM Rev. 23: 308-43
126. Stollery, J. L. 1990. A review of force measurement on delta and caret wings made at Imperial College. Proc. 1st Int. Hypersonic Waverider Symp., Univ. Maryland, College Park Md., Oct. 17-19, 1990
127. Stookesberry, D. C., Tannehill, J. C. 1986. Computation of separated flow on a ramp using the space marching supra-characteristics method. AIAA Pap. 86-0564
128. Sychev, V. V. 1987. Asymptotic Theory of Separated Flows (in Russian). Moscow: Moscow Sci. Pub., Physico-Math. Lit. (Distrib. USSR Nat. Comm. Theor. Appl. Mech.)
129. Tannehill, J. C., Buelow, P. E., Levalts, J. O., Lawrence, S. L. 1990. Three-dimensional upwind parabolized Navier-Stokes codes for real-gas flows. J. Spacecr. Rockets 27: 150-59
130. Thomas, P. D., Neier, K. L. 1990. Navier-Stokes simulation of three-dimensional hypersonic equilibrium flows with ablation. J. Spacecr. Rockets 27: 143-49
131. Townend, L. H. 1991. Research and design of hypersonic aircraft. Philos. Trans. R. Soc. London Ser. A 335: 201-24
132. Treanor, C. E. 1991. Book review: Nonequilibrium Hypersonic Aerothermodynamics, by C. Park. AIAA J. 29: 857-58
133. van Leer, B. 1982. Flux-vector splitting for the Euler equations. Lec. Notes Phys. 170: 507-12
134. van Leer, B., Thomas, J. L., Roe, P. L., Newsome, R. W. 1987. A comparison of numerical flux formulas for the Euler and Navier-Stokes equations. AIAA Pap. 87-1104-CP
135. Vatsa, V. N., Thomas, J. L., Wedan, B. W. 1989. Navier-Stokes computations of a prolate spheroid at angle of attack. J. Aircr. 26: 986-93
136. Vigneron, Y. C., Rakich, J. V., Tannehill, J. C. 1978. Calculation of supersonic viscous flow over delta wings with sharp subsonic leading edges. AIAA Pap. 78-1137
137. Walberg, G. D. 1985. A survey of aeroassisted orbital transfer. J. Spacecr. 22(1): 3-18; also see AIAA Pap. 82-1370
138. Walberg, G. D. 1985. A survey of aeroassisted orbital transfer. J. Spacecr. 22(1): 3-18; also see AIAA Pap. 82-1370
139. Warr, J. 1970. Orbital aerodynamic computer program to calculate force and moment coefficients on complex vehicle configurations. LMSC/HREC D 1624 98 TM 54-20-275, Lockheed, Houston, TX.
140. Weiting, A. 1990. Shock interference heating in scramjet engines. AIAA Pap. 90-5238
141. Werle, M. J., Dwoyer, D. L., Hankey, W. L. 1973. Initial conditions for the hypersonic/boundary-layer problems. AIAA J. 11: 525-30
142. Werle, M. J., Vasta, V. N. 1974. A new method for supersonic boundary layer separation. AIAA J. 12: 1491-97
143. Wilcox, D. C. 1988. Reassessment of the scale determining equations for advanced turbulence models. AIAA J. 26: 1299-1310
144. Wilcox, D. C. 1991. Progress in hypersonic turbulence modelling. AIAA Pap. 91-1785
145. Wilhite, A. W., Arrington, J. P., McCandless, R. S. 1985. Performance aerodynamics of AOTV. In Thermal Design of Aeroassisted Orbital Transfer Vehicle, ed. H. F. Nelson, Progr. Astronaut. Aeronaut. 96: 165-97
146. Williams, R. M. 1986. National Aerospace Plane technology for America's future. Aerosp. Am. 24: 18-22
147. Wilson, G. J., MacCormack, R. W. 1992. Modeling supersonic combustion using a fully implicit numerical method. AIAA J. 30: 1008-15
148. Yee, H. C. 1987. Upwind and symmetric shock-capturing schemes. NASA Tech. Memo. 89464; also see NASA Tech. Memo. 100097
149. Yee, H. C. 1987. Upwind and symmetric shock-capturing schemes. NASA Tech. Memo. 89464; also see NASA Tech. Memo. 100097
150. Ying, S. X., Steger, J. L., Shift, L. B., Baganoff, D. 1986. Numerical simulation of unsteady, viscous, high-angle-of-attack flows using a partially flux split algorithm. AIAA Pap. 86-2179; also see Ying, S. X. 1986. PhD thesis. Stanford Univ.
151. Ying, S. X., Steger, J. L., Shift, L. B., Baganoff, D. 1986. Numerical simulation of unsteady, viscous, high-angle-of-attack flows using a partially flux split algorithm. AIAA Pap. 86-2179; also see Ying, S. X. 1986. PhD thesis. Stanford Univ.
152. Zang, T. A., Dinavahi, S., Piomelli, U. 1989. Reynolds-averaged and subgrid-scale models of transitional flows. 7th NASP Symp., Pap. no. 26
153. Zhong, X., MacCormack, R. W., Chapman, D. R. 1991a. Stabilization of the Burnett equations and application to high-altitude hypersonic flows. AIAA Pap. 91-0770
154. Zhong, X., MacCormack, R. W., Chapman, D. R. 1991b. Evaluation of slip boundary conditions for the Burnett equations with application to hypersonic leading edge flow. Proc. 4th Int. Symp. Comput. Fluid Dynamics, Davis, Calif.