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Tables for correcting airfoil data obtained in the Langley 0.3-meter transonic cryogenic tunnel for sidewall boundary-layer effectsTables for correcting airfoil data taken in the Langley 0.3-meter Transonic Cryogenic Tunnel for the presence of sidewall boundary layer are presented. The corrected Mach number and the correction factor are minutely altered by a 20 percent change in the boundary layer virtual origin distance. The sidewall boundary layer displacement thicknesses measured for perforated sidewall inserts and without boundary layer removal agree with the values calculated for solid sidewalls.
Document ID
19860016817
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Jenkins, R. V.
(NASA Langley Research Center Hampton, VA, United States)
Adcock, J. B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1986
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:87723
NASA-TM-87723
Accession Number
86N26289
Funding Number(s)
PROJECT: RTOP 506-61-01-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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