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Evaluation of scramjet nozzle configurations and film cooling for reduction of wall heatingExperiments on relaminarization, or reverse transition of turbulent flow, have been conducted with a scramjet combustor and nozzle model. The Mach-2.7 direct-connect scramjet combustor employed swept-ramp fuel injectors, and the entering flow simulated Mach-6 to Mach-7 flight conditions. Tests were also conducted without combustor fuel to produce a higher nozzle entrance Mach number and lower pressures. Additional tests were conducted to evaluate the effectiveness of film cooling on the cowl region. At each test condition studied, the entrance radius had no significant effect on the measured downstream wall heating rates. Analysis of the data when fuel was injected into the combustor shows good agreement with turbulent theory; for the tests without fuel injection and combustion, the data downstream of the nozzle entrance radius are intermediate to the calculated turbulent and laminar solutions. Results of film-cooling tests, conducted with both hydrogen and nitrogen injectants, showed that, per unit mass, the hydrogen was approximately three to four times more effective than nitrogen in reducing the downstream wall heating rates.
Document ID
19930037121
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Baker, N. R.
(Lockheed Engineering and Sciences Co. Hampton, VA, United States)
Northam, G. B.
(NASA Langley Research Center Hampton, VA, United States)
Stouffer, S. D.
(Virginia Polytechnic Inst. and State Univ. Blacksburg, United States)
Capriotti, D. P.
(Analytical Services and Materials, Inc. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 93-0744
Meeting Information
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit
Location: Reno, NV
Country: United States
Start Date: January 11, 1993
End Date: January 14, 1993
Sponsors: AIAA
Accession Number
93A21118
Distribution Limits
Public
Copyright
Other

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