An exploratory study of a three-dimensional shock wave turbulent boundary layer interaction in a corner
Author:
Affiliation:
1. Princeton University, NJ
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1991-525
Reference25 articles.
1. +16% +8% +9% .1 - 8% ,918 -6% ,159 -7% 2.94 I. 18" from the plate leading edge:
2. +12% +8% +7% .5 -11% 2.137 -7% ,400 -5% 2.88
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1. Measurements of the triple shock wave/turbulent boundary-layer interaction;AIAA Journal;1996-01
2. Flowfield surveys and computations of a crossing-shock wave/boundary-layer interaction;AIAA Journal;1996-01
3. Inviscid parametric analysis of three-dimensional inlet performance;Journal of Aircraft;1994-05
4. Effects of boundary layer bleed on swept-shock/boundary layer interaction;23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference;1993-07-06
5. Crossing shock wave turbulent boundary layer interactions - Variableangle and shock generator length geometry effects at Mach 3;30th Aerospace Sciences Meeting and Exhibit;1992-01-06
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