Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow-Reference-Cited by-同舟云学术

Detailed Study of Attached and Separated Compression Corner Flowfields in High Reynolds Number Supersonic Flow

Published:1979-06 Issue:6 Volume:17 Page:579-585
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Settles Gary S.¹,Fitzpatrick Thomas J.¹,Bogdonoff Seymour M.¹

Affiliation:

1. Princeton University, Princeton, N.J.

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/3.61180

Reference23 articles.

1. Incipient Separation of a Supersonic Turbulent Boundary Layer at High Reynolds Numbers

2. Details of a Shock-Separated Turbulent Boundary Layer at a Compression Corner

3. Mach 3 oblique shock wave/turbulent boundary layer interactions in three dimensions

4. Dolling, D.S., Cosad, C.D., and Bogdonoff, S.M. "Three-Dimensional Shock Wave Turbulent Boundary Layer Interactions-A Parametric Study of Blunt Fin-Induced Flows," AIAA Paper 78-159, Jan.1978.

5. Dolling, D.S., Cosad, C.D., and Bogdonoff, S.M "'Settles, G.S. "An Experimental Study of Compressible Turbulent Boundary Layer Separation at High Reynolds Number," Ph.D. Dissertation, Aerospace and Mechanical Sciences Dept.Princeton University, Princeton, N.J.Sept. 1975.

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