Upstream Influence in Shock Wave/Transitional Boundary Layer Interactions at Mach 1.8
Author:
Affiliation:
1. The University of Tennessee Space Institute, Tullahoma, Tennessee 37388
2. Purdue University, West Lafayette, Indiana 47907
3. The University of Tennessee, Knoxville, Tennessee 37996
Funder
Office of Naval Research
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
https://arc.aiaa.org/doi/pdf/10.2514/1.J059980
Reference30 articles.
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2. KnightD. D.DegrezG. “Shock Wave Boundary Layer Interactions in High Mach Number Flows: A Critical Survey of Current Numerical Prediction Capabilities,” AGARD Advisory Rept. 319, Vol. 2, Dec. 1998, pp. 1.1–1.35.
3. Progress in shock wave/boundary layer interactions
4. DollingD. S.ClemensN. C.HoodE. “Exploratory Experimental Study of Transitional Shock Wave Boundary Layer Interactions,” Rept. AFRL-SR-AR-TR-03-0046, Jan. 2003.
5. Experimental Studies of Transitional Boundary Layer Shock Wave Interactions
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