An Investigation of Active Flowfield Control for Inlet Shock/Boundary Layer Interaction
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American Institute of Aeronautics and Astronautics
Reference19 articles.
1. 1Wong, W. and Hall, G. “Supperssion of Strong Shock Boundary Layer Interaction in Supersonic Inlets by Boundary Layer Blowing,” AIAA Paper 75-1209, Sept. 1975, AIAA/SAE 11th Propulsion Conference.
2. 2Schwendemann, M. and Sanders, B. “Tangential Blowing for Control of Strong Normal Shock-Boundary Layer Interactions on Inlet Ramps,” AIAA Paper 82-1082, June 1982, AIAA/SAE/ASME 18th Joint Propulsion Conference.
3. 4Mounts, J. and Barber, T. “Numerical Analysis of Shock-Induced Separation Alleviation Using Vortex Generators,” AIAA Paper 92-0751, Jan. 1992, 30th Aerospace Sciences Meeting & Exhibit.
4. 5Jenkins, L., Gorton, S., and Anders, S. “Flow Control Device Evaluation for an Internal Flow with and Adverse Pressure Gradient,” AIAA Paper 2002-0266, Jan. 2002, 40th AIAA Aerospace Sciences Meeting & Exhibit.
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