Results of experiments on unswept slab wing at nominal freestream Mach numbers of 7 and 10 show effect of distortions on heating and surface pressure at angles of attack up to 20°; wing, with both blunt and sharp leading edges, gives results over wide range of local Reynolds and Mach numbers; important alterations to heat-transfer distribution were obtained.
Effect of surface distortions on heat transfer to wing at hypersonic speeds
AIAA J
AIAA Journal ; 1 , n 6
1963
7 pages
Article (Journal)
English
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Hypersonic Heat Transfer on the Upper Wing Surface Fins
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AIAA | 1993
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