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    This article has been cited by the following publications. This list is generated based on data provided by CrossRef.

    Poll, D. I. A. and Hellon, C. M. 1987. An appraisal of ‘flat plate’ closure for the approximate solution of boundary layer problems. The Aeronautical Journal, Vol. 91, Issue. 908, p. 373.

    HEFNER, J. ANDERS, J. and BUSHNELL, D. 1983. 21st Aerospace Sciences Meeting.

    Stollery, J L 1976. Supersonic Turbulent Boundary Layers: Some Comparisons Between Experiment and a Simple Theory. Aeronautical Quarterly, Vol. 27, Issue. 02, p. 87.

    1976. Wall-wake velocity profile for compressible nonadiabatic flows. AIAA Journal, Vol. 14, Issue. 6, p. 820.

    1976. General thermal constriction parameter for annular contacts on circular flux tubes. AIAA Journal, Vol. 14, Issue. 6, p. 822.


The effect of wall cooling on a compressible turbulent boundary layer

  • R. L. Gran (a1) (a2), J. E. Lewis (a1) (a3) and T. Kubota (a4)
  • DOI:
  • Published online: 01 March 2006

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 δTx whereas the case of an adiabatic boundary layer flowing onto a cooled wall gives δTx½. 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.

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Journal of Fluid Mechanics
  • ISSN: 0022-1120
  • EISSN: 1469-7645
  • URL: /core/journals/journal-of-fluid-mechanics
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