Shock tunnel investigation of boundary-layer transition at M equals 5.5.
Author:
Affiliation:
1. Avco Corporation, Wilmington, Mass.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.4098
Reference29 articles.
1. Readers Forum
2. Ferri, A. "Some heat transfer problems in hypersonic flow/7reprinted from Aeronautics and Astronautics (Pergamon Press, New York, 1960), pp.344-377.
3. July 1962;Zakkay V.
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