Micro-Ramp Flow Control of Normal Shock/Boundary Layer Interactions
Author:
Affiliation:
1. University of Illinois at Urbana-Champaign
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2009-920
Reference18 articles.
1. Bodner, J.P., Davis, D.O., Gerber, I., Hingst, W.R. "Experimental Investigation of the Effect of a Single Bleed Hole on a Supersonic Turbulent Boundary-Layer," AIAAPaper 96-2797, July1996.
2. Aktinson, M.D. "Numerical Investigation of a Super-Sonic Inlet Using Bleed and Micro-Ramps to Control Shock-Wave/BoundaryLayer Interactions," AIAA2007-0024.
3. Aerodynamic benefits of adaptive wing technology
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