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Design features and operational characteristics of the Langley 0.3-meter transonic cryogenic tunnelExperience with the Langley 0.3 meter transonic cryogenic tunnel, which is fan driven, indicated that such a tunnel presents no unusual design difficulties and is simple to operate. Purging, cooldown, and warmup times were acceptable and were predicted with good accuracy. Cooling with liquid nitrogen was practical over a wide range of operating conditions at power levels required for transonic testing, and good temperature distributions were obtained by using a simple liquid nitrogen injection system. To take full advantage of the unique Reynolds number capabilities of the 0.3 meter transonic tunnel, it was designed to accommodate test sections other than the original, octagonal, three dimensional test section. A 20- by 60-cm two dimensional test section was recently installed and is being calibrated. A two dimensional test section with self-streamlining walls and a test section incorporating a magnetic suspension and balance system are being considered.
Document ID
19770005128
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Kilgore, R. A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1976
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
NASA-TN-D-8304
L-10950
Accession Number
77N12071
Funding Number(s)
PROJECT: RTOP 505-06-42-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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