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Experimental results for film cooling in 2-D supersonic flow including coolant delivery pressure, geometry, and incident shock effectsAn experimental program was conducted to establish some design parameters important to a supersonic film cooling system in a scramjet engine. A simple non-combusting two-dimensional flow configuration was used to isolate the film cooling phenomena. Parameters investigated include coolant delivery pressure, slot height and lip thickness, and incident shock location and strength. Design guidelines for use in engineering and trade studies are presented.
Document ID
19900032888
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Olsen, George C.
(NASA Langley Research Center Hampton, VA, United States)
Nowak, Robert J.
(NASA Langley Research Center Hampton, VA, United States)
Holden, Michael S.
(Calspan-University of Buffalo Research Center NY, United States)
Baker, N. R.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 90-0605
Accession Number
90A19943
Distribution Limits
Public
Copyright
Other

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