Improvement of conical similarity rule in swept shock wave/boundary layer interaction
Author:
Affiliation:
1. Beijing Univ. of Aeronautics and Astronautics, China
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1993-2941
Reference20 articles.
1. Settles, G. S.,andDolling,D.S.,AIAA progressin Aeronautics and Astronautics, Vol. 104, 1986, 297-379
2. Knight. D.D.Horstmnn, C.C., Shspcy, B. and Bogdonoff,S.M.,AIAAI.25(10), 1987,1331-1337.
3. I Stalker,RJ.AIAA.J.,WllX 1984,16261632.
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3. Correlation of Shock Angles Caused by Rhombic Delta Wings;AIAA Journal;1996-07
4. Incipient turbulent separation induced by swept shock waves;Fluid Dynamics Conference;1994-06-20
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