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CFD simulation of square cross-section, contoured nozzle flows - Comparison with dataComputational analyses have been made of the flow in NASA Langley's Arc-Heated Scramjet Test Facility's Mach 4.7 and Mach 6 square cross-section contoured nozzles, for comparison with experimental results. The analyses, which were performed using a three-dimensional RANS computer code assuming a single species gas with constant specific heats, were intended to provide insight into the nature of the flow development in this type of nozzle. The computational results showed the exit flow distribution to be affected by counter-rotating vortices along the centerline of each nozzle sidewall. Calculated flow properties show general, but not complete, agreement with experimental measurements in both nozzles.
Document ID
19890037668
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Ostrander, Mark J.
(Aerojet TechSystems Co. Sacramento, CA, United States)
Thomas, Scott R.
(Aerojet TechSystems Co. Sacramento, CA, United States)
Voland, Randall T.
(Aerojet TechSystems Co. Sacramento, CA, United States)
Guy, Robert W.
(NASA Langley Research Center Hampton, VA, United States)
Srinivasan, Shivakumar
(Analytical Services and Materials, Inc. Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-0045
Accession Number
89A25039
Distribution Limits
Public
Copyright
Other

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