An experimental/computational study of sharp fin induced shock wave/turbulent boundary layer interactions at Mach 5 - Experimental results
Author:
Affiliation:
1. Texas, University, Austin
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.1992-749
Reference20 articles.
1. Incipient separation of a supersonic turbulent boundary layer at moderate to high Reynolds numbers
2. Prediction of hypersonic shock-wave/turbulent-boundary-layer interaction flows
3. Hypersonic shock-wave turbulent-boundary-layer interaction flows - Experiment and computation
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2. Recent investigations of shock wave effects and interactions;Advances in Aerodynamics;2020-02-07
3. Review and assessment of turbulence models for hypersonic flows;Progress in Aerospace Sciences;2006-10
4. Prediction of Separation Angles Induced by Sharp Fins with Attack Angle;AIAA Journal;2001-11
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