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Computational analysis and preliminary redesign of the nozzle contour of the Langley hypersonic CF4 tunnelA computational analysis, modification, and preliminary redesign study was performed on the nozzle contour of the Langley Hypersonic CF4 Tunnel. This study showed that the existing nozzle was contoured incorrectly for the design operating condition, and this error was shown to produce the measured disturbances in the exit flow field. A modified contour was designed for the current nozzle downstream of the maximum turning point that would provide a uniform exit flow. New nozzle contours were also designed for an exit Mach number and Reynolds number combination which matches that attainable in the Langley 20-Inch Mach 6 Tunnel. Two nozzle contours were designed: one having the same exit radius but a larger mass flow rate than that of the existing CF4 Tunnel, and the other having the same mass flow rate but a smaller exit radius than that of the existing CF4 Tunnel.
Document ID
19870010863
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Thompson, R. A. (NASA Langley Research Center Hampton, VA, United States)
Sutton, Kenneth (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
March 1, 1987
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NASA-TM-89042
L-16170
NAS 1.15:89042
Accession Number
87N20296
Funding Number(s)
PROJECT: RTOP 506-40-11-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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