Experimental study of flow separation on an oscillating flap at Mach 2.4
Author:
Affiliation:
1. University of California, Berkeley, Berkeley, California 94720
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.12440
Reference27 articles.
1. Experiments on Supersonic Boundary-Layer Separation in Three Dimensions
2. Investigation of supersonic separated flow in a compression corner by laser doppler anemometry
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