Computation of Three-Dimensional Turbulent Separated Flows at Supersonic Speeds
Author:
Affiliation:
1. NASA Ames Research Center, Moffett Field, Calif.
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Reference5 articles.
1. Mach 3 oblique shock wave/turbulent boundary layer interactions in three dimensions
2. Peake, D.J."Three-Dimensional Swept Shock/Turbulent Boundary-Layer Separations with Control by Air Injection," National Research Council, Canada, Aeronautic Report LR-592, July 1976.
3. Numerical Solution of Three-Dimensional Shock Wave and Turbulent Boundary-Layer Interaction
4. Computation of three-dimensional turbulent separated flows at supersonic speeds
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