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Experimental results for a hypersonic nozzle/afterbody flow fieldThis study was conducted to experimentally characterize the flow field created by the interaction of a single-expansion ramp-nozzle (SERN) flow with a hypersonic external stream. Data were obtained from a generic nozzle/afterbody model in the 3.5 Foot Hypersonic Wind Tunnel at the NASA Ames Research Center, in a cooperative experimental program involving Ames and McDonnell Douglas Aerospace. The model design and test planning were performed in close cooperation with members of the Ames computational fluid dynamics (CFD) team for the National Aerospace Plane (NASP) program. This paper presents experimental results consisting of oil-flow and shadow graph flow-visualization photographs, afterbody surface-pressure distributions, rake boundary-layer measurements, Preston-tube skin-friction measurements, and flow field surveys with five-hole and thermocouple probes. The probe data consist of impact pressure, flow direction, and total temperature profiles in the interaction flow field.
Document ID
19950016830
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Spaid, Frank W. (McDonnell-Douglas Aerospace Saint Louis, MO., United States)
Keener, Earl R. (Eloret Corp. Palo Alto, CA., United States)
Hui, Frank C. L. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 6, 2013
Publication Date
March 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-4638
NAS 1.15:4638
A-94119
Accession Number
95N23250
Funding Number(s)
PROJECT: RTOP 505-70-62
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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