Experimental Study on Hypersonic Boundary Layer Transition of Re-entry Vehicle HOPE-X

Boundary layer transition is an important subject for the thermal design of re-entry vehicle because aerodynamic heating rate increases very rapidly with the transition. As so many factors affect the boundary layer transition, this subject is still unsolved problem even today, therefore experimental...

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Published inTransactions of the Japan Society of Mechanical Engineers Series B Vol. 64; no. 625; pp. 2915 - 2921
Main Authors SUZUKI, Akio, OGASAWARA, ko
Format Journal Article
LanguageJapanese
Published The Japan Society of Mechanical Engineers 25.09.1998
Subjects
Heat Transfer
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ISSN0387-5016
1884-8346
DOI10.1299/kikaib.64.2915

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Abstract Boundary layer transition is an important subject for the thermal design of re-entry vehicle because aerodynamic heating rate increases very rapidly with the transition. As so many factors affect the boundary layer transition, this subject is still unsolved problem even today, therefore experimental studies are conducted on boundary layer transition of windward surface of HOPE-X. It was ascertained the transition correlation parameter used for Space Shuttle design is applicable as an approximate basis for HOPE-X, though parametric value differs depending on vehicle configuration.
AbstractList Boundary layer transition is an important subject for the thermal design of re-entry vehicle because aerodynamic heating rate increases very rapidly with the transition. As so many factors affect the boundary layer transition, this subject is still unsolved problem even today, therefore experimental studies are conducted on boundary layer transition of windward surface of HOPE-X. It was ascertained the transition correlation parameter used for Space Shuttle design is applicable as an approximate basis for HOPE-X, though parametric value differs depending on vehicle configuration.
Author OGASAWARA, ko
SUZUKI, Akio
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References (5) Malik, M.R., Zang, T. and Bushnell, D., Boundary Layer Transition in Hypersonic Flows, AIAA Paper, 90-5232.
(2) SPACE SHUTTLE AEROTHERODYNAMICS TECHNOLOGY CONFERENCE NASA Tech. Mem., NASA TMX-2507, II-Heating Held at Ames Reserch Center, (1971).
(4) Orr, W. McF., The Stability or Instability of the Steady Motions of a Perfect Liquid and of a Viscous Liquid Proc. R. Irish Acad., 27, 6 (1969), 12-20.
(14) 小笠原宏•鈴木章夫,再突入機の空力加熱分布推定に関する研究,機論,64-625,B(1998),2922-2927.
(16) Hartung, L.C. and Throckmorton, Computer Grophic Visualization of orbiter Lower Surface Boundary Layer Transition, J. Spacecr. Rockets, 24-2 (1987), 109-114.
(7) Arrington, J.P. and Jones, J.J., Shuttle Performance: Lessons Learnd, CP-2283 (1983), NASA.
(6) Test Highlights, AEDC Bull., Arnold Engineering Development Center, Winter, (1993).
(12) Berkowits, A.M. and Kyriss, C.L., Boundary Layers Transition Flight Test Observations, AIAA Paper, 77-125.
(10) Helms, V.T., Evaluation of Boundary-Layer-Transition Criteria for Space Shuttle Orbit Entry, NASA TMX-2507, Proc, Space Shuttle Aerothermodyn. Conf., II-Heating, (1972), 683-704.
(9) Zoby, E.V., Analysis of STS-2 Experimental Heating Rates and Transition Data, J. Spacecr. Rockets, 20-3 (1983), 232-237.
(15) Spalding, D.B. and Chi, Y., The Drag of a Compressible Turbulent Boundary Layer on a Smooth Plate with and without Heat Transfer, J. Fluid Mech., 18 (1964), 117-143.
(3) DeJarnette, F.R, Hamilton, H.H., Weilmuenster, K.J. and Cheatwood, F.M., A Review of Some Approximate Methods Used in Aerodynamic Heating Analysis, J. Thermophy, 1-1 (1987), 5-12.
(13) Wurster, K.E. and Stone, H.W., Aerodynamic Heating Environment Definition/Thermal Protection System Selection for the HL-20, J. Spacecr. Rockets, 30-5 (1993), 549-557.
(1) Anderson, J.D., Jr. Hypersonic and High Temperture Gas Dynamics, (1989), MaGraw Hill Book Co.
(11) Boucutt, K.G., Anderson, J.D., Jr. and Capriotti, D., Viscous Optimized Hypersonic Waveriders, AIAA Paper, 87-0272 (1987).
(8) Zoby, E.V., Moss, J.N. and Sutton, K., Approximate Convective Heating Equations for Hypersonic Flow, J. Spacecr. Rockets, 18-1 (1981), 64-70.
References_xml – reference: (5) Malik, M.R., Zang, T. and Bushnell, D., Boundary Layer Transition in Hypersonic Flows, AIAA Paper, 90-5232.
– reference: (10) Helms, V.T., Evaluation of Boundary-Layer-Transition Criteria for Space Shuttle Orbit Entry, NASA TMX-2507, Proc, Space Shuttle Aerothermodyn. Conf., II-Heating, (1972), 683-704.
– reference: (14) 小笠原宏•鈴木章夫,再突入機の空力加熱分布推定に関する研究,機論,64-625,B(1998),2922-2927.
– reference: (11) Boucutt, K.G., Anderson, J.D., Jr. and Capriotti, D., Viscous Optimized Hypersonic Waveriders, AIAA Paper, 87-0272 (1987).
– reference: (2) SPACE SHUTTLE AEROTHERODYNAMICS TECHNOLOGY CONFERENCE NASA Tech. Mem., NASA TMX-2507, II-Heating Held at Ames Reserch Center, (1971).
– reference: (1) Anderson, J.D., Jr. Hypersonic and High Temperture Gas Dynamics, (1989), MaGraw Hill Book Co.
– reference: (3) DeJarnette, F.R, Hamilton, H.H., Weilmuenster, K.J. and Cheatwood, F.M., A Review of Some Approximate Methods Used in Aerodynamic Heating Analysis, J. Thermophy, 1-1 (1987), 5-12.
– reference: (6) Test Highlights, AEDC Bull., Arnold Engineering Development Center, Winter, (1993).
– reference: (4) Orr, W. McF., The Stability or Instability of the Steady Motions of a Perfect Liquid and of a Viscous Liquid Proc. R. Irish Acad., 27, 6 (1969), 12-20.
– reference: (16) Hartung, L.C. and Throckmorton, Computer Grophic Visualization of orbiter Lower Surface Boundary Layer Transition, J. Spacecr. Rockets, 24-2 (1987), 109-114.
– reference: (7) Arrington, J.P. and Jones, J.J., Shuttle Performance: Lessons Learnd, CP-2283 (1983), NASA.
– reference: (13) Wurster, K.E. and Stone, H.W., Aerodynamic Heating Environment Definition/Thermal Protection System Selection for the HL-20, J. Spacecr. Rockets, 30-5 (1993), 549-557.
– reference: (9) Zoby, E.V., Analysis of STS-2 Experimental Heating Rates and Transition Data, J. Spacecr. Rockets, 20-3 (1983), 232-237.
– reference: (8) Zoby, E.V., Moss, J.N. and Sutton, K., Approximate Convective Heating Equations for Hypersonic Flow, J. Spacecr. Rockets, 18-1 (1981), 64-70.
– reference: (12) Berkowits, A.M. and Kyriss, C.L., Boundary Layers Transition Flight Test Observations, AIAA Paper, 77-125.
– reference: (15) Spalding, D.B. and Chi, Y., The Drag of a Compressible Turbulent Boundary Layer on a Smooth Plate with and without Heat Transfer, J. Fluid Mech., 18 (1964), 117-143.
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Snippet Boundary layer transition is an important subject for the thermal design of re-entry vehicle because aerodynamic heating rate increases very rapidly with the...
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SubjectTerms Heat Transfer
Title Experimental Study on Hypersonic Boundary Layer Transition of Re-entry Vehicle HOPE-X
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