Experimental Study of a Mach 3 Compression Ramp Interaction at Re{theta} = 2400
Author:
Affiliation:
1. Princeton University, Princeton, New Jersey 08544
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.38248
Reference45 articles.
1. Incipient Separation of a Supersonic Turbulent Boundary Layer at High Reynolds Numbers
2. Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow
3. Unsteadiness of the Separation Shock Wave Structure in a Supersonic Compression Ramp Flowfield
4. The Structure of Turbulence in a Supersonic Shock-Wave/Boundary-Layer Interaction
5. Turbulent boundary-layer properties downstream of the shock-wave/boundary-layer interaction
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