Experimental Studies on Micro-Vortex Generator Controlled Shock/Boundary-Layer Interactions in Mach 2.2 Intake-Reference-Cited by-同舟云学术

Experimental Studies on Micro-Vortex Generator Controlled Shock/Boundary-Layer Interactions in Mach 2.2 Intake

Published:2019-04-23 Issue:3 Volume:20 Page:584-595
ISSN:2093-274X
Container-title:International Journal of Aeronautical and Space Sciences
language:en
Short-container-title:Int. J. Aeronaut. Space Sci.

Author:

Kaushik Mrinal^ORCID

Publisher

Springer Science and Business Media LLC

Subject

Electrical and Electronic Engineering,Aerospace Engineering,General Materials Science,Control and Systems Engineering

Link

http://link.springer.com/content/pdf/10.1007/s42405-019-00166-5.pdf

Reference19 articles.

1. Delery JM (1985) Shock-wave/turbulent boundary-layer interaction and its control. Prog Aerosp Sci 22(4):209–280

2. Seddon J, Goldsmith EL (1985) Intake aerodynamics. AIAA education series, New York (ISBN 9781563473616)

3. Délery, J., Marvin, J.G., and Reshotko, E. (1986), “Shock-wave boundary layer interactions”, (No. AGARD-AG-280), Advisory Group for Aerospace Research and Development, France

4. Hamed A, Shang JS (1991) Survey of validation database for shockwave boundary-layer interactions in supersonic inlets. J Propul Power 7(4):617–625

5. Donaldson, C.D., and Lange, R.H. (1952), “Study of the pressure rise across shock waves required to separate laminar and turbulent boundary layers”, NACA-TN-2770, National Advisory Committee for Aeronautics

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