Analysis of Shockwave/Turbulent Boundary Layer Interaction Using DNS and Experimental Data
Author:
Affiliation:
1. Princeton Univ.
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2005-310
Reference28 articles.
1. New Experimental Data of STBLI at DNS/LES Accessible Reynolds Numbers
2. 2Selig, M. S., Unsteadiness of Shock Wave/Turbulent Boundary Layer Interactions with Dynamic Control, Ph.D. thesis,Princeton University, 1988.
3. Details of a Shock-Separated Turbulent Boundary Layer at a Compression Corner
4. Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow
5. Investigation of Three-Dimensional Shock/Boundary-Layer Interactions at Swept Compression Corners
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