Direct Numerical Simulation of Supersonic Turbulent Boundary Layer over a Compression Ramp
Author:
Affiliation:
1. Princeton University, Princeton, New Jersey 08540
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.27021
Reference40 articles.
1. Details of a Shock-Separated Turbulent Boundary Layer at a Compression Corner
2. Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow
3. Investigation of Three-Dimensional Shock/Boundary-Layer Interactions at Swept Compression Corners
4. Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield
5. Unsteadiness of the shock wave structure in attached and separated compression ramp flowfields
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