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Experimental study of nozzle wall boundary layers at Mach numbers 20 to 47The nozzle wall boundary layer of an M-50 helium tunnel was investigated with pitot pressure, total temperature, skin friction, and wall heat transfer measurements at five stations and hot wire measurements at two stations. The results indicated that the boundary layer was turbulent with a thick viscous sublayer. Pressure gradients were observed across the boundary layer; the effect of these gradients on the equations of motion are discussed. The direct skin friction measurements were higher than expected from empirical predictions; the Reynolds analogy factors however were lower than expected. Hot wire measurements indicated mass flow fluctuations as large as 80 percent of the local mean mass flow at the edge of the viscous sublayer with a maximum value relative to the edge mass flow of about 15 percent at gamma about equal to 0.8.
Document ID
19730002534
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Kemp, J. H., Jr. (NASA Ames Research Center Moffett Field, CA, United States)
Owen, F. K. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 2, 2013
Publication Date
October 1, 1972
Subject Category
Fluid Mechanics
Report/Patent Number
A-4359
NASA-TN-D-6965
Accession Number
73N11261
Funding Number(s)
PROJECT: RTOP 136-13-01-16-00-21
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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