Supersonic turbulent flow past a swept compression corner at Mach 3.II
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/10.2514/6.1988-310
Reference8 articles.
1. Feni A, 'Experimental Results with Airfoils Tested in the High-speed Tunnel at Guidonin". NASA TM 946 (translation). 1940.
2. AIAA Progress m Astronautics and Aeronautics Series.;Settles G..,1986
3. The Interaction Between Boundary Layer and Shock Waves in Transonic Flow
4. Ackeret. I. Feldman, F. and Rott. N. 'Investigations of Compression Shocks and Boundary Layers in Gases Movmg at High Speeds". NASA TM 1113. 1947.
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