Reynolds number effects in swept-shock-wave/turbulent-boundary-layer interaction
Author:
Affiliation:
1. Cambridge University, Cambridge CB2 1PZ, England, United Kingdom
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/3.12649
Reference29 articles.
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5. Conical similarity of shock/boundary-layer interactions generated byswept and unswept fins
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1. Incipient separation in shock wave/boundary layer interactions as induced by sharp fin;Shock Waves;2006-07-22
2. Active Control of Swept Shock Wave / Boundary Layer Interactions;Drag Reduction by Shock and Boundary Layer Control;2002
3. A REVIEW OF THE ROLE OF SOME SMALL HIGH-SPEED WIND TUNNELS IN AERONAUTICAL RESEARCH;Progress in Aerospace Sciences;1998-03
4. An Investigation of Passive Control Applied to Swept Shock-Wave / Boundary-Layer Interactions;Notes on Numerical Fluid Mechanics (NNFM);1997
5. Shock waves/turbulent boundary-layer interactions - Fundamental studies and applications;Fluid Dynamics Conference;1996-06-17
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