Mach 8 to 22 studies of flow separations due to deflected control surfaces
Author:
Affiliation:
1. Boeing Company, Seattle, Wash
2. University of Washington, Seattle, Wash
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.2289
Reference18 articles.
1. March 1962;Kaufman L G
2. Sterrett, J R and Emery, J C , 'Extension of boundarylayer separation criteria to a Mach number of 6 5 by utilizing flat plates with forward-facing steps, ' NASA TND 618 (Decem ber 1960)
3. October 1959;Bogdonoff S M
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