Shock tunnel investigation of boundary-layer transition at M equals 5.5.
RUSHTON, G. H. /AVCO CORP., AEROPHYSICS DEPT., WILMINGTON, MASS./., STETSON, K. F.
AIAA Journal ; 5 , 5 ; 899-906
1967
Article (Journal)
Electronic Resource
English
Shock tunnel investigation of boundary-layer transition at M = 5.5
Engineering Index Backfile | 1967
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