NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Experimental and computational study of the effect of shocks on film cooling effectiveness in scramjet combustorsThis paper presents results from a study conducted to investigate the effect of incident oblique shocks on the effectiveness of a coolant film at Mach numbers, typical of those expected in a scramjet combustor at Mach 15 to 20 flight. Computations with a parabolic code are in good agreement with the measured pressures and heat fluxes, after accounting for the influence of the shock upstream of its point of impingement on the plate, and the expansion from the trailing edge of the shock generator. The test data shows that, for the blowing rates tested, the film is rendered largely ineffective by the shock. Computations show that coolant blowing rates five to ten times those tested are required to protect against shock-induced heating. The implications of the results to scramjet combustor design are discussed.
Document ID
19900051360
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kamath, Pradeep S.
(Analytical Services and Materials, Inc. Hampton, VA, United States)
Holden, Michael S.
(Calspan-State University of New York Research Center Buffalo, United States)
Mcclinton, Charles R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
June 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-1713
Accession Number
90A38415
Distribution Limits
Public
Copyright
Other

Available Downloads

There are no available downloads for this record.
No Preview Available