Turbulent boundary-layer properties downstream of the shock-wave/boundary-layer interaction-Reference-Cited by-同舟云学术

Turbulent boundary-layer properties downstream of the shock-wave/boundary-layer interaction

Published:1987-05 Issue:5 Volume:25 Page:668-675
ISSN:0001-1452
Container-title:AIAA Journal
language:en
Short-container-title:AIAA Journal

Author:

Kuntz D. W.¹,Amatucci V. A.²,Addy A. L.²

Affiliation:

1. Sandia National Laboratories, Albuquerque, New Mexico

2. University of Illinois at Urbana-Champaign, Urbana, Illinois

Publisher

American Institute of Aeronautics and Astronautics (AIAA)

Subject

Aerospace Engineering

Link

http://arc.aiaa.org/doi/pdf/10.2514/3.9681

Reference27 articles.

1. z, D.W. "An Experimental Investigation of the Shock Wave-Turbulent Boundary Layer Interaction," Ph.D. Thesis, Dept. of Mechanical and Industrial Engineering,Univ. of Illinoisat Urbana-Champaign, Urbana,1985.

2. 2Settles, G.S. "An Experimental Study of Compressible Turbulent Boundary Layer Separation at High Reynolds Numbers," Ph.D. Thesis,Princeton Univ., Princeton, NewJersey,1975.

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

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

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

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