Aeroheating measurement of Apollo shaped capsule with boundary layer trip in the free-piston shock tunnel HIEST
Author:
Affiliation:
1. Japan Aerospace Exploration Agency (JAXA)
2. NASA Johnson Space Center
3. NASA Ames Research Center
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2014-0434
Reference16 articles.
1. Hypersonic aerothermodynamic and scramjet research using high enthalpy shock tunnel
2. 2Hornung, H.G. and Belanger, J. "Role and techniques of ground testing for simulation of flows up to orbital speed", AIAA Paper No.1990-1377.
3. 5Hollis, B.R., Berger, K.T., Horvath, T.J., Coblish, J.J., Norris, J.D., Lillard, R.P., and Kirk, B.S. "Aeroheating testing and prediction for project Orion CEV at turbulent condition", AIAA Paper No.2008-1226.
4. 6Amar, A.J., Horvath, T.J., Hollis, B.R., Berger, K.T., Berry, S.A. "Protuberance boundary layer transition for project Orion crew entry vehicle", AIAA Paper No.2008-1227.
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