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Similarity rule for sidewall boundary-layer effects in airfoil testingThe simplified form of the similarity rule for sidewall boundary layer effects presented envisions the generation of changes in both airfoil thickness and freestream Mach number by the sidewall boundary layer. Within the small-disturbance approximation, this approach encompasses the methods of both Barnwell (1980) and Sewall (1982), and can accordingly be applied at speeds ranging from the lowest to transonic Mach numbers.
Document ID
19880032020
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Murthy, A. V.
(Old Dominion University Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
November 1, 1987
Publication Information
Publication: AIAA Journal
Volume: 25
ISSN: 0001-1452
Subject Category
Aerodynamics
Accession Number
88A19247
Funding Number(s)
CONTRACT_GRANT: NAS1-334
Distribution Limits
Public
Copyright
Other

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