Concave Bump for Impinging-Shock Control in Supersonic Flows
Author:
Affiliation:
1. German Aerospace Center DLR, Institute of Aerodynamics and Flow Technology, Göttingen, 37073, Germany
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J060799
Reference21 articles.
1. GoldbergT. J.HefnerJ. N. “Starting Phenomena for Hypersonic Inlets with Thick Turbulent Boundary Layers at Mach 6,” NASA TN D-6280, 1971.
2. Starting characteristics of supersonic inlets
3. Progress in Astronautics and Aeronautics;Van Wie D. M.,2001
4. Bleed System Design Technology for Supersonic Inlets
5. SlaterJ. “CFD Methods for Computing the Performance of Supersonic Inlets,” AIAA Paper 2004-3404, 2004.
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