Film Cooling With Normal Injection Into a Supersonic Flow

[+] Author and Article Information
R. J. Goldstein, E. R. G. Eckert, D. J. Wilson

School of Mechanical and Aerospace Engineering, University of Minnesota, Minneapolis, Minn.

J. Eng. Ind 90(4), 584-588 (Nov 01, 1968) (5 pages) doi:10.1115/1.3604692 History: Received March 21, 1968; Online August 25, 2011


An experimental study of film cooling with subsonic gas injection into a mainstream with a Mach number of 2.90 is reported. Air, used as both the mainstream and secondary fluids, is injected normal to the surface of a flat plate through a short porous section into a two-dimensional turbulent boundary layer. The secondary fluid enters the boundary layer with a mass velocity which ranges from 0.0085 to 0.0223 of the free-stream value. The adiabatic wall temperatures are presented as the film-cooling effectiveness. The results of the present study, when the proper choice is made for the reference state used to account for fluid property variations across the high-speed boundary layer, are in good agreement with previous investigations in incompressible flows.

Copyright © 1968 by ASME
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