Shock tunnel investigation of boundary-layer transition at M equals 5.5.
- 1 May 1967
- journal article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in AIAA Journal
- Vol. 5 (5) , 899-906
- https://doi.org/10.2514/3.4098
Abstract
No abstract availableKeywords
This publication has 6 references indexed in Scilit:
- BOUNDARY-LAYER TRANSITION ON A HIGHLY COOLED 10 DEGREE CONE IN HYPERSONIC FLOWSPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1964
- Transition Reversal and Tollmien—Schlichting InstabilityPhysics of Fluids, 1963
- Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flowsJournal of Fluid Mechanics, 1962
- Use of the Roughness Criterion to Refute Roughness as the Cause of Reported Transition ReversalJournal of the Aerospace Sciences, 1960
- Experiments on Boundary-Layer Transition at Supersonic SpeedsJournal of the Aeronautical Sciences, 1957
- Readers ForumJournal of the Aeronautical Sciences, 1954