Deriving Features of Reacting Hypersonic Flow from Gradients at a Curved Shock
Author:
Affiliation:
1. California Institute of Technology, Pasadena, California 91125
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.39993
Reference22 articles.
1. Oswatitsch, K., Gasdynamik, Springer-Verlag, Berlin, 1952.
2. XVIII. The flow behind a stationary shock
3. Surface-Pressure Gradient and Shock-Front Curvature at the Edge of a Plane Ogive with Attached Shock Front
4. Calculation of Flow-Variable Gradients Behind Curved Shock Waves
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