Journal of Fluid Mechanics

The effect of wall cooling on a compressible turbulent boundary layer

R. L.  Gran a1p1, J. E.  Lewis a1p2 and T.  Kubota a2
a1 TRW Systems Group, Redondo Beach, California
a2 California Institute of Technology, Pasadena

Article author query
gran rl   [Google Scholar] 
lewis je   [Google Scholar] 
kubota t   [Google Scholar] 


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 [similar] x whereas the case of an adiabatic boundary layer flowing onto a cooled wall gives δT [similar] x[fraction one-half]. 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.

(Published Online March 29 2006)
(Received October 5 1973)

p1 Present address: Flow Research, Inc., Los Angeles, California.
p2 Present address: Techmate, Inc., Torrance, California.

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