Heat transfer rate for laminar, transition and turbulent boundary layer and transition phenomenon on shock tube wall-Reference-Cited by-同舟云学术

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Heat transfer rate for laminar, transition and turbulent boundary layer and transition phenomenon on shock tube wall

Published:1982-01-11 Issue: Volume: Page:
ISSN:
Container-title:20th Aerospace Sciences Meeting
language:
Short-container-title:

Author:

DILLON, JR. R.¹,NAGAMATSU H.²

Affiliation:

1. U.S. Army, Benet Weapons Laboratory, Watervliet,NY

2. Rensselaer Polytechnic Institute, Troy, NY

Publisher

American Institute of Aeronautics and Astronautics

Link

http://arc.aiaa.org/doi/pdf/10.2514/6.1982-32

Reference12 articles.

1. E.J. Gion, "A Tracer Study of the Shock Tube Boundary Iayer," Ph.D. Thesis,Iehigh University, 1965.

2. W.P. Thompson, "An Experimental Study of Turbulent Spots and wall Roughness Effects in Shock Tube Boundary Layer Transition," Ph.D. Thesis,Iehigh University, 1963.

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