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The effect of wall cooling on a compressible turbulent boundary layer

Published online by Cambridge University Press:  29 March 2006

R. L. Gran ,
J. E. Lewis  and
T. Kubota
R. L. Gran
Affiliation:
TRW Systems Group, Redondo Beach, California Present address: Flow Research, Inc., Los Angeles, California.
J. E. Lewis
Affiliation:
TRW Systems Group, Redondo Beach, California Present address: Techmate, Inc., Torrance, California.
T. Kubota
Affiliation:
California Institute of Technology, Pasadena
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Abstract

Experimental results are presented for two turbulent boundary-layer experiments conducted at a free-stream Mach number of 4 with wall cooling. The first experiment examines a constant-temperature cold-wall boundary layer subjected to adverse and favourable pressure gradients. It is shown that the boundary-layer data display good agreement with Coles’ general composite boundary-layer profile using Van Driest's transformation. Further, the pressuregradient parameter βK found in previous studies to correlate adiabatic highspeed data with low-speed data also correlates the present cooled-wall high-speed data. The second experiment treats the response of a constant-pressure highspeed boundary layer to a near step change in wall temperature. It is found that the growth rate of the thermal boundary layer within the existing turbulent boundary layer varies considerably depending upon the direction of the wall temperature change. For the case of an initially cooled boundary layer flowing onto a wall near the recovery temperature, it is found that δT ∼ x whereas the case of an adiabatic boundary layer flowing onto a cooled wall gives δT ∼ x½. The apparent origin of the thermal boundary layer also changes considerably, which is accounted for by the variation in sublayer thicknesses and growth rates within the sublayer.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 66 , Issue 3 , 25 November 1974 , pp. 507 - 528
Copyright
© 1974 Cambridge University Press

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