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Turbulent shear stresses in compressible boundary layersHot-wire anemometer measurements of turbulent shear stresses in a Mach 3 compressible boundary layer were performed in order to investigate the effects of heat transfer on turbulence. Measurements were obtained by an x-probe in a flat plate, zero pressure gradient, two dimensional boundary layer in a wind tunnel with wall to freestream temperature ratios of 0.94 and 0.71. The measured shear stress distributions are found to be in good agreement with previous results, supporting the contention that the shear stress distribution is essentially independent of Mach number and heat transfer for Mach numbers from incompressible to hypersonic and wall to freestream temperature ratios of 0.4 to 1.0. It is also found that corrections for frequency response limitations of the electronic equipment are necessary to determine the correct shear stress distribution, particularly at the walls.
Document ID
19790057741
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Laderman, A. J.
(Ford Aerospace and Communications Corp. Newport Beach, CA, United States)
Demetriades, A.
(Ford Aerospace and Communications Corp. Aeronutronic Div., Newport Beach, Calif., United States)
Date Acquired
August 9, 2013
Publication Date
July 1, 1979
Publication Information
Publication: AIAA Journal
Volume: 17
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
79A41754
Funding Number(s)
CONTRACT_GRANT: DAAG29-75-C-0014
Distribution Limits
Public
Copyright
Other

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