Microramp Flow Control for Oblique Shock Interactions: Comparisons of Computational and Experimental Data
Author:
Affiliation:
1. NASA Glenn Research Center
2. University of Florida
3. University of Notre Dame
Publisher
American Institute of Aeronautics and Astronautics
Link
http://arc.aiaa.org/doi/pdf/10.2514/6.2010-4973
Reference16 articles.
1. 1Fukuda, M. K., Hingst, W. G., Reshotko, E. "Control of Shock Wave-BoundaryLayer Interactions byBleed in Supersonic Mixed Compression Inlets,"NASACR2595,1975.
2. 2Young, D. D., Jenkins, S. A. "An Investigation of Active Flowfield Control for Inlet Shock/Boundary Layer Interaction," AIAAPaper 2005-4020,July2005.
3. Review of research on low-profile vortex generators to control boundary-layer separation
4. 4Anderson, B.H., Tinapple, J., Surber, L. "Optimal Control of Shock Wave Turbulent Boundary Layer Interactions Using Micro-ArrayActuation,"AIAAPaper 2006-3197,June2006.
5. 5Hirt,S.M.,Anderson,B.H."ExperimentalInvestigationoftheApplicationofMicrorampFlowControltoanObliqueShock Interaction,"AIAAPaper 2009-919, Jan 2009.
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