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Turbulent-boundary-layer heat-transfer and transition measurements with surface cooling at Mach 6Wall cooling effects on turbulent heat transfer and boundary layer transition for sharp leading edge flat plate at hypersonic speeds
Document ID
19700022486
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Cary, A. M., Jr. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
June 1, 1970
Subject Category
Fluid Mechanics
Report/Patent Number
L-6825
NASA-TN-D-5863
Report Number: L-6825
Report Number: NASA-TN-D-5863
Accession Number
70N31797
Funding Number(s)
CONTRACT_GRANT: 129-01-20-09
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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