Research conducted on effects of wall cooling, Mach and unit Reynolds number on transition R number of cylindrical, separated boundary layers on ogive-cylinder model; results obtained from pressure and temperature measurements and shadowgraph observations.
Transition Reynolds numbers of separated flows at supersonic speeds
NASA -- Tech Note
1960
39 pages
Aufsatz (Zeitschrift)
Englisch
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Asymmetric separated flows at supersonic speeds
AIAA | 1992
|Asymmetric separated flows at supersonic speeds
Tema Archiv | 1992
|Asymmetric separated flows at supersonic speeds
AIAA | 1990
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