Interaction between the Unsteady Boundary Layer and Inviscid Hot Flow in a Shock Tube
Author:
Affiliation:
1. University of Provence, St. Jerome Center, Marseille, France
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.61233
Reference20 articles.
1. Shock-Tube Performance at Low Initial Pressure
2. On Flow Duration in Low-Pressure Shock Tubes
3. Testing Time and Contact-Zone Phenomena in Shock-Tube Flows
4. Test Time in Low-Pressure Shock Tubes
5. Series solutions for shock tube laminar boundary layer and test time.
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