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A Determination of the Laminar-, Transitional-, and Turbulent-boundary-layer Temperature-recovery Factors on a Flat Plate in Supersonic Flow
Document ID
19930082751
Acquisition Source
Legacy CDMS
Document Type
Other
Authors
Stalder, Jackson R
Rubesin, Morris W
Tendeland, Thorval
Date Acquired
August 16, 2013
Publication Date
June 1, 1950
Report/Patent Number
NACA-TN-2077
Report Number: NACA-TN-2077
Accession Number
93R12041
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
BOUNDARY LAYER - TEMPERATURE
BOUNDARY LAYER - PLATES, FLAT EFFECT OF TEMPERATURE
WIND TUNNELS - AAL - HEAT TRANSFER, SUPERSONIC (6') (AMER )
WIND TUNNEL TESTS - AAL - HEAT TRANSFER, SUPERSONIC (6')
BOUNDARY LAYER - VELOCITY DISTRIBUTION
BOUNDARY LAYER TRANSITION - PLATES, FLAT
FLOW VELOCITY, HIGH - SUPERSONIC
HEAT TRANSMISSION - BOUNDARY LAYER
BOUNDARY LAYER - PLATES, FLAT LAMINAR
BOUNDARY LAYER - PLATES, FLAT TURBULENT

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