In design of hypersonic space vehicles with ramjet propulsion, location of transition is important for heat transfer and performance of hypersonic inlets; however, there is no reliable theory to predict transition over 8 Mach; investigation was conducted in hypersonic shock tunnel at 8.5 to 10.5 Mach number range with stagnation temperature of 1400 K; experimental results obtained and comparison of transition Reynolds number are presented.
Boundary-layer transition on 10° cone in hypersonic flows
AIAA J
AIAA Journal ; 3 , n 11
1965
8 pages
Aufsatz (Zeitschrift)
Englisch
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