Flight test measurements of boundary-layer transition on a nonablating 22 deg cone
- 1 February 1970
- journal article
- research article
- Published by American Institute of Aeronautics and Astronautics (AIAA) in Journal of Spacecraft and Rockets
- Vol. 7 (2) , 137-142
- https://doi.org/10.2514/3.29888
Abstract
No abstract availableKeywords
This publication has 7 references indexed in Scilit:
- Shock tunnel investigation of boundary-layer transition at M equals 5.5.AIAA Journal, 1967
- Ratio on base pressure.AIAA Journal, 1965
- Hypersonic boundary-layer transition data for a cold-wall slender coneAIAA Journal, 1965
- Flat plate boundary layer transition at hypersonic speedsPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1965
- Recent Studies of the Laminar Base-Flow RegionAIAA Journal, 1964
- BOUNDARY-LAYER TRANSITION ON A HIGHLY COOLED 10 DEGREE CONE IN HYPERSONIC FLOWSPublished by American Institute of Aeronautics and Astronautics (AIAA) ,1964
- Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flowsJournal of Fluid Mechanics, 1962