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Local turbulent skin-friction measurements on a flat plate at mach numbers from 2.5 to 4.5 and reynolds numbers up to 69 x 106Supersonic wind tunnel tests of turbulent skin friction on flat plate at very high Reynolds number
Document ID
19650018215
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Allen, J. M. (NASA Langley Research Center Hampton, VA, United States)
Monta, W. J. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
July 1, 1965
Subject Category
Aerodynamics
Report/Patent Number
NASA-TN-D-2896
Report Number: NASA-TN-D-2896
Accession Number
65N27816
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
REYNOLDS NUMBER
SKIN FRICTION
SUPERSONIC WIND TUNNEL
FLAT PLATE

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