Supersonic turbulent flow past a 3-D swept compression corner at Mach 3
Author:
Affiliation:
1. Rutgers University, New Brunswick, NJ
2. NASA, Ames Research Center, Moffett Field, CA
3. Princeton University, NJ
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1987-551
Reference39 articles.
1. Three-Dimensional Shock Wave-Turbulent Boundary Layer Interactions at Mach 6
2. Experimental studies of quasi-two-dimensional and three-dimensional viscous interaction regions induced by skewed-shock and swept-shock boundary layer interaction
3. Knight, D., Horstman, C., Shapey, 8. and Bogdonoff, S. "The Flowfield Structure of the 3-0Shock Wave-Boundary Layer Interaction Generated by a 20 deq Sharp Fin at Mach 3," AIM Paper No. 86-0343,1986.
4. Horstman, C., and Hung, C. "Computation of Three-Dimensional Turbulent Separated Flows at Supersonic Speeds, "AIAA Paper No. 79-0002, 1979.
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