Laminar-turbulent transition on reentry capsules and planetary probes

Journal of Spacecraft and Rockets

Volumn 43, Issue 6, 2006, Pages 1153-1173

  Schneider, Steven P ^a,b,c  

^a PURDUE UNIVERSITY   (United States)

^b Aeronautical and Astronautical Engineering

^c AIAA   (United States)

Author keywords

[No Author keywords available]

Indexed keywords

HEAT SHIELDING; PRODUCT DEVELOPMENT; REENTRY; SPACE PROBES; SPACECRAFT;

ABLATION EFFECTS; PLANETARY PROBES; RE-ENTRY SPACE VEHICLES; SHEAR LAYERS;

AERODYNAMICS;

EID: 33846116031     PISSN: 00224650     EISSN: 15336794     Source Type: Journal    
DOI: 10.2514/1.22594     Document Type: Review

References (117)

1. Aldridge, E. C., Jr., Fiorina, C. S., Jackson, M. P., Leshin, L. A., Lyles, L. L., Spudis, P. D., Tyson, N. D., Walker, R. S., and Zuber, M. T., "A Journey to Inspire, Innovate, and Discover," Report of the President's Commission on Implementation of the United States Space Policy, June 2004, www.nasa.gov/pdf/60736main_M2M_report_small.pdf [cited 3 Oct. 2006].
2. Griffin, M. D., and French, J. R., Space Vehicle Design, 2nd ed., AIAA, Reston, VA, 2004.
3. Anderson, J. D., Hypersonic and High Temperature Gas Dynamics, McGraw-Hill, New York, 1989; Reprinted by AIAA, Reston, VA, 2000.
4. Schneider, S. P., "Hypersonic Laminar-Turbulent Transition on Circular Cones and Scramjet Forebodies," Progress in Aerospace Sciences, Vol. 40, Nos. 1-2, 2004, pp. 1-50.
5. Coleman, W. D., Hearne, L. F., Lefferdo, J. M., and Vojvodich, N. S., "A Study of the Effects of Environmental and Ablator Performance Uncertainties on Heat Shielding Requirements for Blunt and Slender Hyperbolic-Entry Vehicles," AIAA Paper 68-154, Jan. 1968.
6. Hall, R. D., and Shayler, D. J., Soyuz: A Universal Spacecraft, Springer, London, 2003.
7. Schneider, S. P., "Laminar-Turbulent Transition on Reentry Capsules and Planetary Probes," AIAA Paper 2005-4763, June 2005.
8. Beckwith, I. E., and Miller, C. G., III, " Aerothermodynamics and Transition in High-Speed Wind Tunnels at NASA Langley," Annual Review of Fluid Mechanics, Vol. 22, 1990, pp. 419-439.
9. Schneider, S. P., "Effects of High-Speed Tunnel Noise on Laminar-Turbulent Transition," Journal of Spacecraft and Rockets, Vol. 38, No. 3, May-June 2001, pp. 323-333.
10. Schneider, S. P., "Flight Data for Boundary-Layer Transition at Hypersonic and Supersonic Speeds," Journal of Spacecraft and Rockets, Vol. 36, No. 1, 1999, pp. 8-20.
11. Reda, D. C., "Review and Synthesis of Roughness-Dominated Transition Correlations for Reentry Applications," Journal of Spacecraft and Rockets, Vol. 39, No. 2, March-April 2002, pp. 161-167.
12. Pate, S. R., "Supersonic Boundary-Layer Transition: Effects of Roughness and Freestream Disturbances," AIAA Journal, Vol. 9, No. 5, May 1971, pp. 797-803.
13. Johnson, H., Candler, G. V., and Wright, M. J., "Boundary Layer Stability Analysis of Mars Science Laboratory Aeroshell," AIAA Paper 2006-0920, Jan. 2006.
14. Horvath, T. J., Berry, S. A., and Merski, N. R., "Hypersonic Boundary/ Shear Layer Transition for Blunt to Slender Configurations - ANASA Langley Experimental Perspective," Enhancement of NATO Military Flight Vehicle Performance by Management of Interacting Boundary Layer Transition and Separation, NATO RTO-MP-AVT-111, Oct. 2004; also Paper AVT-111-22, presented at the Applied Vehicle Technology Panel and Specialist's meeting, Prague, Czech Republic.
15. Wright, M. J., Brown, J. L., Sinha, K., Candler, G. V., Milos, F. S., and Prabhu, D. K., "Validation of Afterbody Aeroheating Predictions for Planetary Probes: Status and Future Work," NASA, Technical Report CP 2004-213456, Aug. 2004, pp. 275-285.
16. Wright, M. J., Milos, F. S., and Tran, P., "Survey of Afterbody Aeroheating Flight Data for Planetary Probe Thermal Protection System Design," AIAA Paper 2005-4815, June 2005.
17. Edquist, K. T., Liechty, D. S., Hollis, B. R., Alter, S. J., and Loomis, M. P., "Aeroheating Environments for a Mars Smart Lander," AIAA Paper 2002-4505, Aug. 2002.
18. Edquist, K. T., Liechty, D. S., Hollis, B. R., Alter, S. J., and Loomis, M. P., "Aeroheating Environments for a Mars Smart Lander," Journal of Spacecraft and Rockets, Vol. 43, No. 2, March-April 2006, pp. 330-339.
19. Horvath, T. J., Heiner, N. C., Olguin, D. M., Cheatwood, F. M., and Gnoffo, P. A., "Afterbody Heating Characteristics of a Proposed Mars Sample Return Orbiter," AIAA Paper 2001-3068, June 2001.
20. Horvath, T. J., Heiner, N. C., and Olguin, D. M., "Wake Closure and Afterbody Heating on a Mars Sample Return Orbiter," Journal of Spacecraft and Rockets, Vol. 41, No. 5, Sept.-Oct. 2004, pp. 705-715.
21. Smith, A., "Entry and Vehicle Design Considerations," Capsule Aerothermodynamics, AGARD R-808, March 1995.
22. Sinha, K., Bamhardt, M., and Candler, G. V., "Detached Eddy Simulation of Hypersonic Base Flows with Application to Fire II Experiments," AIAA Paper 2004-2633, June 2004.
23. Sommer, S. C., Short, B. J., and Compton, D. L., "Free-Flight Measurements of Static and Dynamic Stability of Models of the Project Mercury Re-Entry Capsule at Mach Numbers 3 and 9.5," NASA, Technical Memorandum TM-X-373, Aug. 1960.
24. Taylor, N. L., Hodge, W. F., and Burbank, P. B., "Heat-Transfer and Pressure Measurements of a 1/7-Scale Model of a Mercury Capsule at Angles of Attack from 0 to 20 deg at Mach Numbers of 3.50 and 4.44," NASA, Technical Memorandum TM-X-522, June 1961.
25. Everhart, P. E., and Bemot, P. T., "Measurements of the Surface Flows, Heat Transfer, Pressure Distribution, and Longitudinal Stability of a Mercury Capsule Model at Mach Numbers of 6.9 and 9.6," NASA, Technical Memorandum TM-X-458, April 1961.
26. Relier, J. O., Jr., and Seegmiller, H. L., "Pressure and Heat-Transfer Measurements on a Mercury Capsule Model," NASA, Technical Memorandum TM-X-647, May 1962.
27. Erb, R. B., and Jacobs, S., "Entry Performance of the Mercury Spacecraft Heat Shield," NASA TM-X-57097, STI citation 66N15350, Oct. 1964.
28. O'Neal, R. L., and Rabb, L., "Heat-Shield Performance During Atmospheric Entry of Project Mercury Research and Development Vehicle," NASA, Technical Memorandum TM-X-490, May 1961.
29. Stephens, E. W., "Afterbody Heating Data Obtained from an Atlas-Boosted Mercury Configuration in a Free Body Reentry," NASA, Technical Memorandum TM-X-493, Aug. 1961.
30. Western, K. C., and Swanson, J. E., "A Compilation of Wind-Tunnel Heat-Transfer Measurements on the Afterbody of the Project Mercury Capsule Reentry Configuration," NASA, Technical Memorandum TM-X-495, Aug. 1961.
31. Murphy, J. D., "Flight Test Aerodynamic Heating Data for the Afterbody of the Project Mercury Spacecraft with Comparisons to Available Prediction Methods," NASA, Technical Report CR-649, June 1967.
32. Kruse, R. L., Malcolm, G. N., and Short, B. J., "Comparison of Free-Flight Measurements of Stability of the Gemini and Mercury Capsules at Mach Numbers 3 and 9.5," NASA, Technical Memorandum TM-X-957, April 1964.
33. Mitchell, W. S., Maynard, O. E., and Arabian, D. D., "Gemini Results as Related to the Apollo Program," Gemini Summary Conference, NASA SP-138, Feb. 1967, pp. 329-336.
34. Box, D. M., Harpold, J. C., Paddock, S. G., Armstrong, N. A., and Hamby, W. H., "Controlled Reentry," Gemini Summary Conference, NASA SP-138, Feb. 1967, pp. 159-166.
35. Griffith, B. J., "Comparison of Aerodynamic Data from the Gemini Flights and AEDC-VKF Wind Tunnels,"Journal of Spacecraft and Rockets, Vol. 4, No. 7, July 1967, pp. 919-924.
36. Pershing, B. M., "The Hypersonic Aerodynamic Characteristics of the Gemini Re-Entry Module Based on a Statistical Analysis of Wind Tunnel Test Data," Aerospace Corporation, Aerospace Report TOR-0150(3107-15)-8, June 1968, DTIC citation AD856691.
37. Bertin, J. J., and Cummings, R. M., "Fifty Years of Hypersonics: Where We've Been, Where We're Going," Progress in Aerospace Sciences, Vol. 39, Nos. 6-7, Aug.-Oct. 2003, pp. 511-536.
38. Malik, P. W., and Souris, G. A., "Project Gemini: A Technical Summary," NASA, Contractor Report CR-1106, June 1968.
39. Collins, D. R., Dotts, H. W., Hoyler, W. F., and Hecht, K. F., "Spacecraft Development," Gemini Midprogram Conference, Including Experiment Results, NASA SP-121, Feb. 1966, pp. 15-23.
40. Gemini Program, "Gemini Program Mission Report GT-2, Gemini 2," NASA, Technical Memorandum NASA-TM-X-57103, Feb. 1965, NASA citation 75N75478.
41. Sheldon, G. J., "Re-Entry Module/Adaptor Interconnect Fairing Aerodynamic Heating Wind Tunnel Tests AEDC Tunnel B," McDonnell Company, Final report, Dec. 1967, DTIC citation AD-856658.
42. Anon., "Gemini-B Re-Entry Module/Adaptor Attachment Fairing Aerodynamic Heating and Pressure Tests in the McDonnell Hypervelocity Impulse Tunnel-Series I," McDonnell Company, Technical Report MAC-O004-Vol-1, Dec. 1967, DTIC citation AD-856900.
43. Anon., "Gemini-B Re-Entry Module/Adaptor Attachment Fairing Aerodynamic Heating and Pressure Tests in the McDonnell Hypervelocity Impulse Tunnel-Series 1," McDonnell Company, Technical Report MAC-G004-Vol-2, Dec. 1967, DTIC citation AD-856901.
44. Raper, R. M., "Heat-Transfer and Pressure Measurements Obtained During Launch and Reentry of the First Four Gemini-Titan Missions and Some Comparisons with Wind-Tunnel Data," NASA Technical Memorandum TM-X-1407, Aug. 1967.
45. Pritts, O. R., and Merz, G. H., "Pressure and Heat-Transfer Distributions on Exit and Re-Entry Configurations of the Gemini Spacecraft at Mach Number 8 and 10," AEDC Technical Report AEDC-TDR-63-100, July 1963.
46. Price, E. A., Jr., Stallings, R. L., Jr., and Howard, P. W., "Pressure and Heat-Transfer Distributions of 0.1-Scale Gemini Exit and Reentry Models at Mach Numbers of 3.51 and 4.44," NASA Technical Memorandum TM-X-1149, Sept. 1965.
47. Kruse, R. L., "Transition and Flow Reattachment Behind an Apollo-Like Body at Mach Numbers to 9," NASA Technical Note TN-D-4645, July 1968.
48. Wright, M. J., Prabhu, D. K., and Martinez, E. R., "Analysis of Afterbo'dy Heating Rates on the Apollo Command Modules, Part 1 : AS-202," AIAA Paper 2004-2456, June 2004.
49. Canning, T. N., and Sommer, S. C., "Investigation of Boundary-Layer Transition on Flat-Faced Bodies of Revolution at High Supersonic Speeds," NACA Research Memorandum RM-A57C25, June 1957, NASA STI citation 93R18985.
50. Walters, E. W., "Free-Flight Measurements of Radiative Heating to the Front Face of the Apollo Reentry Capsule as a Function of Angle of Attack," NASA, Technical Memorandum NASA-TM-X-851, Feb. 1964.
51. Chapman, G. T., and Jackson, C. T., Jr., "A Free-Flight Investigation of the Heat Transfer and Afterbody Flow Field of an Apollo-Type Configuration at Speeds to 10,000 ft/sec," NASA Technical Memorandum NASA-TM-X-853, Nov. 1963.
52. Crowder, R. S., and Moote, J. D., "Apollo Entry Aerodynamics," AIAA Paper 68-1008, Oct. 1968.
53. Graves, C. A., and Harpold, J. C., "Re-Entry Targeting Philosophy and Flight Results from Apollo 10 and 11," AIAA Paper 70-28, Jan. 1970.
54. Low, G., "Apollo 11 Mission Report," NASA Technical Report MSC-00171, 1969, NASA citation 70N17401.
55. Honegger, B., and Brandli, H., "Saving Apollo 11," Aviation Week and Space Technology, Dec. 2004, pp. 79-80.
56. Hillje, E. R., "Entry Flight Aerodynamics from Apollo Mission AS-202," NASA Technical Note NASA-TN-D-4185, Oct. 1967.
57. Hillje, E. R., "Entry Aerodynamics at Lunar Return Conditions Obtained from the Flight of Apollo 4 (AS-501)," NASA Technical Note NASA-TN-D-5399, Oct. 1969.
58. Griffith, B. J., and Boylan, D. E., "Postflight Apollo Command Module Aerodynamic Simulation Tests," Journal of Spacecraft and Rockets, Vol. 5, No. 7, July 1968, pp. 843-848.
59. Griffith, B. J., and Boylan, D. E., "Reynolds and Mach Number Simulation of Apollo and Gemini Re-Entry and Comparison with Flight," Hypersonic Boundary Layers and Flow Fields. AGARD CP-30, Paper 8.
60. Hillje, E. R., and Savage, R., "Status of Aerodynamic Characteristics of the Apollo Entry Configuration," AIAA Paper 68-1143, Dec. 1968.
61. Graves, C. A., and Harpold, J. C., "Apollo Experience Report-Mission Planning for Apollo Entry," NASA Technical Note NASA-TN-D-6725, March 1972.
62. Harpold, J. C., "Minimum Lift-to-Drag Ratio Requirement for the Lunar Mission," NASA Technical Memorandum NASA-TM-X-69752, Oct. 1967, NASA STI citation 74N70848.
63. Berry, S. A., Horvath, T. J., Weilmuenster, K. J., Alter, S. J., and Merski, N. R., "X-38 Experimental Aeroheating at Mach 10," AIAA Paper 2001-2828, June 2001.
64. Bell Comm. Co., "Some Effects on the Apollo Mission of Reducing the Maximum Reentry Range," NASA Contractor Report NASA-CR-111052, June 1964, NASA citation 79N71907.
65. Pavlosky, J. E., and St. Leger, L. G., "Apollo Experience Report - Thermal Protection Subsystem," NASA Technical Note NASA-TN-D-7564, Jan. 1974.
66. Erb, R. B., Greenshields, D. H., Chauvin, L. T., Pavlosky, J. E., and Statham, C. L., "Apollo Thermal-Protection System Development," Journal of Spacecraft and Rockets. Vol. 7, No. 6, June 1970, pp. 727-734.
67. Erb, R. B., Greenshields, D. H., Chauvin, L. T., Pavlosky, J. E., and Statham, C. L., "Apollo Thermal-Protection System Development," AIAA Paper 68-1142, Dec. 1968.
68. Anon. (North American Aviation Staff), "Design Criteria, Trajectories, and Heating Rates for the Apollo Command Module Heat Shield, Volume 1," NASA Technical Report CR-117561, June 1963; NASA STI citation 79N76584.
69. Lee, D. B., "Trajectory Influence on the Heating Distribution Around the Apollo Command Module," NASA Technical Memorandum NASA-TM-X-65127, May 1965.
70. Bertin, J. J., "Wind-Tunnel Heating Rates for the Apollo Spacecraft," NASA Technical Memorandum NASA-TM-X-1033, Jan. 1965 (limited distribution).
71. Weston, K. C., and Fitzkee, A. L., "Afterbody Heat Transfer Measurements Obtained During Reentry of the Spacecraft of the Mercury-Atlas 5 Mission," NASA Technical Memorandum NASA-TM-X-564, Dec. 1963 (limited distribution).
72. Jones, R. A., "Wind-Tunnel Measurements of Transition on the Face of a Blunt Entry Capsule at Angle of Attack," AIAA Journal, Vol. 6, No. 3, March 1968, pp. 545-546.
73. Jones, R. A., "Measured Heat-Transfer and Pressure Distributions on the Apollo Face at a Mach Number of 8 and Estimates for Flight Conditions," NASA Technical Memorandum NASA-TM-X-919, April 1964.
74. Jones, R. A., "Preliminary Results on Heat-Transfer to the Afterbody of the Apollo Reentry Configuration at a Mach Number of 8," NASA Technical Memorandum NASA-TM-X-699, Sept. 1962; Superseded by NASATM-X-813.
75. Jones, R. A., "Experimental Investigation of the Overall Pressure Distribution, Flow Field, and Afterbody Heat-Transfer Distribution of an Apollo Reentry Configuration at a Mach Number of 8," NASA Technical Memorandum NASA-TM-X-813, June 1963; Supersedes NASA TM-X-699.
76. Jones, J. J., and Moore, J. A., "Shock-Tunnel Heat Transfer Investigation on the Afterbody of an Apollo-Type Configuration at Angles of Attack up to 45 deg," NASA Technical Memorandum NASA-TM-X-1042, Dec. 1965.
77. Marvin, J. G., Tendeland, T., and Kussoy, M., "Apollo Forebody Pressure and Heat-Transfer Distributions in Helium at Mach 20," NASA Technical Memorandum NASA-TM-X-854, Nov. 1963.
78. Lees, L., "Laminar Heat Transfer over Blunt-Nosed Bodies at Hypersonic Flight Speeds," Jet Propulsion, Vol. 26, April 1956. pp. 259-269.
79. Marvin, J. G., and Kussoy, M., "Experimental Investigation of the Flow Field and Heat-Transfer over the Apollo-Capsule Afterbody at a Mach Number of 20," NASA Technical Memorandum NASA-TM-X-1032, Feb. 1965.
80. Lee, G., "Correlation of Heat-Transfer Data for the Apollo Afterbody at Mach Numbers 8 to 20," NASA Technical Memorandum NASA-TM-X-855, Feb. 1964.
81. Bertin, J. J., Lee, D. E., and Ried, R. C., "Apollo Reentry Heating," NASA Technical Memorandum NASA-TM-X-66780, Sept. 1963, NASA STI citation 79N76503.
82. Smith, A. M. O., and Clutter, D. W., "The Smallest Height of Roughness Capable of Affecting Boundary-Layer Transition," Journal of the Aerospace Sciences, Vol. 26, No. 4, April 1959, pp. 229-245.
83. Bertin, J. J., "The Effect of Protuberances, Cavities, and Angle of Attack on the Wind-Tunnel Pressure and Heat-Transfer Distribution for the Apollo Command Module," NASA Technical Memorandum NASA-TM-X-1243, Oct. 1966.
84. Mosely, W. C., Jr., and Martino, J. C., "Apollo Wind Tunnel Testing Program-Historical Development of General Configurations," NASA Technical Note NASA-TN-D-3748, Dec. 1966.
85. Yee, L., "Free-Flight Measurements of Heat Transferred to the Apollo Afterbody with and Without Heat Shield Ablation," NASA Technical Memorandum NASA-TM-X-1096, April 1965.
86. Lee, D. B., "Apollo Experience Report-Aerothermodynamics Evaluation," NASA Technical Note NASA-TN-D-6843, June 1972.
87. Lee, D. B., Bertin, J. J., and Goodrich, W. D., "Heat-Transfer Rate and Pressure Measurements Obtained During Apollo Orbital Entries." NASA Technical Note NASA-TN-D-6028, Oct. 1970.
88. Lee, D. B., and Goodrich, W. D., "The Aerothermodynamic Environment of the Apollo Command Module During Superorbital Entry," NASA Technical Note NASA-TN-D-6792, April 1972.
89. Bartlett, E. P., Nicolet, W. E., Abbett, M. J., and Moyer, C. B., "Improved Heat-Shield Design Procedures for Manned Entry Systems. Part 2; Application to Apollo; Final Report," NASA Contractor Report NASA-CR-108689, June 1970, NASA citation 94N71373.
90. Bartlett, E. P., "Improved Heat-Shield Design Procedures for Manned Entry systems. Part 1: Executive Summary; Final Report," NASA Contractor Report NASA-CR-108688, June 1970, NASA citation 94N71374.
91. Bartlett, E. P., and Curry, D. M., "An Evaluation of Flight Data for the Apollo Thermal Protection System," Space Simulation, NASA SP298, May 1972, pp. 749-768.
92. Williams, S. D., Curry, D. M., Bouslog, S. A., and Rochelle, W. C., "Thermal Protection System Design Studies for Lunar Crew Module," Journal of Spacecraft and Rockets, Vol. 32, No. 3, May-June 1995, pp. 456-462.
93. Park, C., and Tauber, M. E., "Heatshielding Problems of Planetary Entry, a Review." AIAA Paper 99-3415, June 1999.
94. Milos, F. S., "Galileo Probe Heat Shield Ablation Experiment," Journal of Spacecraft and Rockets, Vol. 34, No. 6, Nov.-Dec. 1997, pp. 705-713.
95. Milos, F. S., Chen, Y.-K., Squire, T. H., and Brewer, R. A., "Analyis of Galileo Probe Heatshield Ablation and Temperature Data," Journal of Spacecraft and Rockets, Vol. 36, No. 3, May-June 1999, pp. 298-306.
96. Zappa, O. L., and Reinecke, W. G., "An Experimental Investigation of Base Heating on Typical Mars Entry Body Shapes," NASA Technical Report NASA-CR-1920, Nov. 1971.
97. Little, H. R., and Boudreau, A. H., "Heat-Transfer Tests on a 14-Percent Scale Model of the NASA-MMC Viking Mars Entry Vehicle at Mach Number 16," AEDC, Technical Report AEDC-TR-73-195, Dec. 1973.
98. Edquist, K. T., Wright, M. J., and Allen, G. A., Jr., "Viking Afterbody Heating Computations and Comparisons to Flight Data," AIAA Paper 2006-0386, Jan. 2006.
99. Lockwood, M. K., Sutton, K., Prabhu, R., Powell, R. W., Graves, C. A., Epp, C., and Carman, G. L., "Entry Configurations and Performance Comparisons for the Mars Smart Lander," AIAA Paper 2002-4407, Aug. 2002.
100. Hollis, B. R., Liechty, D. S., Wright, M. J., Holden, M. S., Wadhams, T. P., MacLean, M., and Dyakonov, A., "Transition Onset and Turbulent Heating Measurements for the Mars Science Laboratory Entry Vehicle," AIAA Paper 2005-1437, Jan. 2005.
101. Horvath, T. J., O'Connell, T. F., Cheatwood, F. M., Alter, S. J., and Prabhu, R. K., "Experimental Hypersonic Aerodynamic Characteristics of the 2001 Mars Surveyor Precision Lander with Flap," AIAA Paper 2002-4408, Aug. 2002.
102. Edquist, K. T., and Alter, S. J., "Computational Aeroheating Predictions for Mars Lander Configurations," AIAA Paper 2003-3639, June 2003.
103. Wright, M. J., Olejniczak, J., Brown, J. L., Homung, H. G., and Edquist, K. T., "Computational Modeling of T5 Laminar and Turbulent Heating Data on Blunt Cones, Part 2: Mars Applications," AIAA Paper 2005-0177, Jan. 2005.
104. 2 Test Gas Including Catalytic Effects," AIAA Paper 2005-4693, June 2005.
105. Komurasaki, K., and Candler, G. V., "Theoretical Consideration on Laminar-to-Turbulent Transitions over an Ablating Reentry Capsule," Japanese Institute of Space and Astronautical Science, Technical Report SP-17, March 2003, NASA citation 20040003940
106. Kaattari, G. E., "Effects of Mass Addition on Blunt-Body Boundary-Layer Transition and Heat Transfer," NASA Technical Report NASA-TP-1139, Jan. 1978.
107. Park, C, and Balakrishnan, A., "Ablation of Galileo Probe Heat-Shield Models in a Ballistic Range," AIAA Journal, Vol. 23, No. 2, Feb. 1985, pp. 301-308.
108. Yamada, T., Ogawa, H., Nonaka, S., Inatani, Y., Nakakita, K., and Yamazaki, T., "An Experimental Study on the Boundary Layer Transition Due to Gas Injection from Capsule-Shape Body Surface," Japanese Institute of Space and Astronautical Science, Technical Report SP-17, March 2003, NASA citation 20040003942.
109. Sawada, K., "Anomalous Heating Profile over Entry Capsule with Ablation and its Relation to Earlier Turbulent Transition," Japanese Institute of Space and Astronautical Science, Technical Report SP-17, March 2003, NASA citation 20040003941.
110. Milos, F. S., "Galileo Probe Heat Shield Ablation Experiment," AIAA Paper 96-1823, June 1996.
111. Park, C., Abe, T., and Inatani, Y., "Research on the Heatshield for MUSES-C Earth Reentry," AIAA Paper 98-2852, June 1998.
112. Suzuki, K., and Abe, T., "Experimental Studies on Boundary-Layer Transition on a Reentry Vehicle at Transonic and Supersonic Speeds," Japanese Institute of Space and Astronautical Science, Technical Report 659, March 1995, NASA citation 95N29712.
113. Suzuki, K., and Abe, T., "Wind Tunnel Experiments on Wake Flow Field Behind a Reentry Capsule from a Viewpoint of Parachute Deployment at Supersonic Speeds," Japanese Institute of Space and Astronautical Science, Technical Report 655, Dec. 1994, NASA citation 95N26740.
114. Olejniczak, J., Wright, M. J., Laurence, S., and Hornung, H. G., "Computational Modeling of T5 Laminar and Turbulent Heating Data on Blunt Cones, Part 1: Titan Applications," AIAA Paper 2005-0176, Jan. 2005.
115. Beckwith, I. E., and Bertram, M. H., "A Survey of NASA Langley Studies on High-Speed Transition and the Quiet Tunnel," NASA, Technical Report TMTX-2566, July 1972, NASA Recon citation 72N26239.
116. Berkowitz, A. M., Kyriss, C. L., and Martellucci, A., "Boundary Layer Transition Flight Test Observations," AIAA Paper 77-125, Jan. 1977.
117. Reshotko, E., "Transition Issues at Hypersonic Speeds," AIAA Paper 2006-0707, Jan. 2006.