Experimental Investigations of Mach 3 Shock-Wave Turbulent Boundary Layer Interactions
Author:
Affiliation:
1. Princeton University
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2005-4899
Reference25 articles.
1. Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow
2. Turbulent boundary-layer properties downstream of the shock-wave/boundary-layer interaction
3. Experimental study of three shock wave/turbulent boundary layer interactions
4. The Structure of Turbulence in a Supersonic Shock-Wave/Boundary-Layer Interaction
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