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Supersonic and hypersonic quiet tunnel technology at NASA LangleyQuiet tunnel technology at NASA Langley is reviewed focusing on historical background, basic quiet tunnel concepts, design methodology, and significant results. Each of the NASA Langley quiet tunnels and recent flow quality results for a refurbished Mach 6 quiet nozzle are presented. It is concluded that high-speed quiet tunels should be viewed as a required adjunct to computational and experimental tools being developed to explore issues of instability and transition physics. The quiet tunnel technology can produce and maintain an adequately smooth nozzle finish, control settling chamber disturbances, and keep the facility clean and is capable of adequately measuring flow disturbances.
Document ID
19920074119
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Wilkinson, S. P.
(NASA Langley Research Center Hampton, VA, United States)
Anders, S. G.
(NASA Langley Research Center Hampton, VA, United States)
Chen, F.-J.
(NASA Langley Research Center Hampton, VA, United States)
Beckwith, I. E.
(Joint Institute for Applied Flight Sciences; NASA, Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
July 1, 1992
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 92-3908
Accession Number
92A56743
Funding Number(s)
CONTRACT_GRANT: NAS1-18458
Distribution Limits
Public
Copyright
Other

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