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The cryogenic wind tunnel for high Reynolds number testingThe development of cryogenic wind tunnels is reviewed with reference to the theory and advantages of cryogenic tunnels, problems common to wind tunnels and their solution, and application of cryogenic wind tunnels to high Reynolds number testing. It is shown that cryogenic wind tunnels can achieve full-scale Reynolds number with reasonable tunnel size, dynamic pressure, and drive power; the use of such tunnels also makes it possible to separate the effects of Reynolds number, Mach number, and aeroelasticity. Application of the cryogenic tunnel concept is illustrated by three examples, namely an atmospheric low-speed cryogenic tunnel, a 0.3-meter transonic cryogenic tunnel, and the National Transonic Facility now nearing completion.
Document ID
19820049785
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kilgore, R. A.
(NASA Langley Research Center Hampton, VA, United States)
Dress, D. A.
(Kentron Technical Center Hampton, VA, United States)
Date Acquired
August 10, 2013
Publication Date
May 1, 1982
Subject Category
Research And Support Facilities (Air)
Meeting Information
Meeting: National Aerospace Laboratory
Location: Tokyo
Country: Japan
Start Date: May 20, 1982
Accession Number
82A33320
Distribution Limits
Public
Copyright
Other

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