Effects of nose bluntness, angle of attack, and boundary-layer cooling on boundary-layer transition on 8° half-angle cone are presented; small amount of bluntness was found to displace transition location rearward; greater amounts produced blunting transition reversal in that rearward movement of transition ceased and additional blunting produced forward displacement; maximum rearward displacement from cone tip was about 4.1 times that of sharp cone; data obtained are tabulated.
Shock tunnel investigation of boundary-layer transition at M = 5.5
AIAA J
AIAA Journal ; 5 , n 5
1967
8 pages
Aufsatz (Zeitschrift)
Englisch
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