Lee surface flow phenomena over Space Shuttle at large angles of attack at M infinity = 6
Author:
Affiliation:
1. New York University, Westbury, N.Y.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1975-148
Reference31 articles.
1. Vol. 6, No. 12, Dee. 1968, pp. 2380-2387.
2. Alleviation of vortex-induced heating to the lee side of slender wings in hypersonic flow
3. Hypersonic lee-surface heating alleviation on delta wing by apex-drooping
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2. Flow separation on a spheroid at incidence;Journal of Fluid Mechanics;1979-06-27
3. Effects of surface temperature and Reynolds number on heat transfer to the Shuttle Orbiter leeward fuselage;14th Aerospace Sciences Meeting;1976-01-26
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