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Reynolds-shear-stress measurements in a compressible boundary layer within a shock-wave-induced adverse pressure gradient

Published online by Cambridge University Press:  29 March 2006

W. C. Rose  and
M. E. Childs
W. C. Rose
Affiliation:
Ames Research Center, NASA, Moffett Field, California 94035
M. E. Childs
Affiliation:
University of Washington, Seattle, Washington 98195
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Abstract

The results of an experimental investigation of the mean- and fluctuating-flow properties of a compressible turbulent boundary layer in a shock-wave-induced adverse pressure gradient are presented. The turbulent boundary layer developed on the wall of an axially symmetric nozzle and test section whose nominal free-stream Mach number and boundary-layer-thickness Reynolds number were 4 and 105, respectively. The adverse pressure gradient was induced by an externally generated, conical shock wave.

Mean and time-averaged fluctuating-flow data, including the experimental Reynolds shear stresses and experimental turbulent heat-transfer rates, are presented for the boundary layer and external flow, upstream, within and downstream of the pressure gradient. The turbulent mixing properties of the flow were determined experimentally with a hot-wire anemometer. The calibration of the wires and the interpretation of the data are discussed.

From the results of the investigation, it is concluded that the shock-wave/boundary-layer interaction significantly alters the shear-stress characteristics of the boundary layer.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 65 , Issue 1 , 12 August 1974 , pp. 177 - 188
Copyright
© 1974 Cambridge University Press

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