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Heat transfer from a hypersonic turbulent boundary layer on a flat plate

Published online by Cambridge University Press:  29 March 2006

G. T. Coleman ,
C. Osborne  and
J. L. Stollery
G. T. Coleman
Affiliation:
Department of Aeronautics, Imperial College, London
C. Osborne
Affiliation:
Department of Aeronautics, Imperial College, London
J. L. Stollery
Affiliation:
Department of Aeronautics, Imperial College, London
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Abstract

A hypersonic gun tunnel has been used to measure the heat transfer to a sharpedged flat plate inclined at various incidences to generate local Mach numbers from 3 to 9. The measurements have been compared with a number of theoretical estimates by plotting the Stanton number against the energy-thickness Reynolds number. The prediction giving the most reasonable agreement throughout the above Mach number range is that due to Fernholz (1971).

The values of the skin-friction coefficient derived from velocity profiles and Preston tube data are also given.

Type
Research Article
Information
Journal of Fluid Mechanics , Volume 60 , Issue 2 , 4 September 1973 , pp. 257 - 271
Copyright
© 1973 Cambridge University Press

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References

Batham, J. P. 1972 An experimental study of turbulent separating and reattaching flows at high Mach numbers J. Fluid Mech. 52, 425.Google Scholar
Coleman, G. T. 1972 Tabulated heat transfer rate data for a hypersonic turbulent boundary layer over a flat plate. Imperial College Aero. Rep. no. 72–06.Google Scholar
Eaton, C. J., Pederson, J. R. C., Plane, C. G. & Southgate, A. C. 1969 Experimental studies at Mach numbers of 3, 4 and 5 of turbulent boundary-layer heat transfer in two-dimensional flows with pressure gradient. Brit. Aircraft Co. Rep. ST 2310. (See also Corrigendum.)Google Scholar
Eckert, E. R. G. 1955 Engineering relations for friction and heat transfer to surfaces in high velocity flow J. Aero. Sci. 22, 585.Google Scholar
Fernholz, H. 1971 Ein halbempirischen Gesetz für die Wandreibung in kompressiblen turbulenten Grenzschichten bei isothermer und adiabater Wand Z. angew. Math. Mech. 1, 146–147.Google Scholar
Gibson, M. M. & Spalding, D. B. 1971 Application of the k-W model of turbulence to boundary layers with streamwise pressure gradients, large temperature variations, and transpiration cooling. Imperial College, Dept. Mech. Engng Rep. EHT/TN/A/32.Google Scholar
Green, J. E. 1972 Application of Head's entrainment method to the prediction of turbulent boundary layers and wakes in compressible flow. R.A.E. Tech. Rep. no. 72079.Google Scholar
Harvey, W. D. & Clark, F. L. 1972 Measurements of skin friction on the wall of a hypersonic nozzle A.I.A.A. J. 10, 1256.Google Scholar
Hastings, R. C. & Sawyer, W. G. 1970 Turbulent boundary layers on a large flat plate at M = 4. R.A.E. Tech. Rep. no. 70040.Google Scholar
Hopkins, E. J., Keener, E. R., Polek, J. E. & Dwyer, H. A. 1972 Hypersonic turbulent skin-friction and boundary layer profiles on nonadiabatic flat plates A.I.A.A. J. 10, 40–48.Google Scholar
Hopkins, E. J., Rubesin, M. W., Inouye, M., Keener, E. R., Mateer, G. C. & Polek, T. E. 1969 Summary and correlation of skin friction and heat transfer data for a hypersonic turbulent boundary layer on simples shapes. N.A.S.A. Tech. Note, D-5089.Google Scholar
Keener, E. R. & Hopkins, E. J. 1969 Use of Preston tubes for measuring hypersonic turbulent skin friction. N.A.S.A. Tech. Note, D-5544.Google Scholar
Needham, D. A., Elfstrom, G. M. & Stollery, J. L. 1970 Design and operation of the Imperial College no. 2 hypersonic gun tunnel. Imperial College Aero. Rep. no. 70–04.Google Scholar
Patankar, S. V. & Spalding, D. B. 1970 Heat and Mass Transfer in Boundary Layers, 2nd edn. London: Intertext.
Sivasegaram, S. 1971 The evaluation of local skin friction in compressible flow Roy. Aero. Soc. Aero. J. 75, 793.Google Scholar
Spalding, D. B. & Chi, S. W. 1964 The drag of a compressible turbulent boundary layer on a smooth flat plate with and without heat transfer J. Fluid Mech. 18, 117.Google Scholar
Van Driest, E. R. 1956 Problem of aerodynamic heating Aeron. Engng Rev. 15, 26.Google Scholar