Shock Tube as a Device for Testing Transonic Airfoils at High Reynolds Numbers
Author:
Affiliation:
1. low a State University, Ames, Iowa
2. NASA Ames Research Center, Moffett Field, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.61208
Reference15 articles.
1. Shock-Tube Studies of Transonic Flow over Wedge Profiles
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