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Wind-tunnel measurements and comparison with flight of the boundary layer and heat transfer on a hollow cylinder at Mach 3The wind tunnel tests were conducted both with and without boundary layer trips at Mach 3 and nominal free stream Reynolds numbers per meter ranging from 3.3 x 10 the 6th power. Instrumentation consisted of pressure orifices, thermocouples, a boundary layer pitot pressure rake, and a floating element skin friction balance. Measurements from both wind tunnel and flight were compared with existing engineering prediction methods.
Document ID
19810006460
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Stallings, R. L., Jr. (NASA Langley Research Center Hampton, VA, United States)
Lamb, M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
L-14044
NASA-TP-1789
Accession Number
81N14975
Funding Number(s)
PROJECT: RTOP 505-43-23-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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