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30 degree injectors at hypervelocity conditionsResults are presented of the first high-speed propulsion-related experiments performed in the NASA-Ames 16-Inch Shock Tunnel, designed to simulate combustor inlet conditions at approximately Mach 14. Results demonstrate the capability of the tunnel for high-speed propulsion testing and yield data on the performance of 30-deg flush wall injectors tested in the tunnel. The experimental results are compared with those of a CFD analysis.
Document ID
19920066253
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Loomis, Mark P. (MCAT Institute San Jose, CA, United States)
Zambrana, Horacio A. (NASA Ames Research Center Moffett Field, CA, United States)
Bogdanoff, David W. (Eloret Institute Palo Alto, CA, United States)
Tam, Tim C. (NASA Ames Research Center Moffett Field, CA, United States)
Cavolowsky, John A. (NASA Ames Research Center Moffett Field, CA, United States)
Newfield, Mark E. (NASA Ames Research Center Moffett Field, CA, United States)
Bittner, Robert D. (Analytical Services and Materials, Inc. Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Fluid Mechanics And Heat Transfer
Report/Patent Number
AIAA PAPER 92-3288
Accession Number
92A48877
Funding Number(s)
CONTRACT_GRANT: NCC2-487
CONTRACT_GRANT: NCC2-738
Distribution Limits
Public
Copyright
Other

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