Flight test measurements of boundary-layer transition on a nonablating 22 deg cone
Author:
Affiliation:
1. Philco-Ford Corporation, Newport Beach, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Space and Planetary Science,Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/3.29888
Reference10 articles.
1. Shock tunnel investigation of boundary-layer transition at M equals 5.5.
2. Flat plate boundary layer transition at hypersonic speeds
3. BOUNDARY-LAYER TRANSITION ON A HIGHLY COOLED 10 DEGREE CONE IN HYPERSONIC FLOWS
4. Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flows
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