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
1967-01-01
8 pages
Article (Journal)
Electronic Resource
English
Numerical Investigation on Transition of Shock Induced Boundary Layer
British Library Conference Proceedings | 2009
|