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NASA Lewis 8 by 6 foot supersonic wind tunnelPerformance data are presented for the tunnel, which has a Mach number range from 0.36 to 2.0. The tunnel circuit, test section, model support systems, auxiliary systems, instrumentation, control room equipment, and automatic recording and computing equipment are also described. Information is presented on criteria for designing models and on shop facilities available to prospective users.
Document ID
19740017676
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Swallow, R. J. (NASA Lewis Research Center Cleveland, OH, United States)
Aiello, R. A. (NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Subject Category
Facilities, Research, And Support
Report/Patent Number
NASA-TM-X-71542
E-7949
Accession Number
74N25789
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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