Numerical and Experimental Investigations of the Supersonic Microramp Wake
Author:
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Subject
Aerospace Engineering
Link
http://arc.aiaa.org/doi/pdf/10.2514/1.J052649
Reference22 articles.
1. Separation control on high-lift airfoils via micro-vortex generators
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3. YaoC.S.LinJ. C.AllanB. G. “Flow-Field Measurement of Device-Induced Embedded Streamwise Vortex on a Flat Plate,” AIAA Paper 2002-3162, 2002.
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5. Effect of Microvortex Generators On Seperated Normal Shock/ Boundary Layer Interactions
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4. Planar laser scattering visualization of streamwise vortex pairs in a Mach 6 flow;Chinese Journal of Aeronautics;2023-01
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