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Some heat transfer measurements in compressible turbulent boundary layers

Published online by Cambridge University Press:  04 July 2016

T. Hughes
T. Hughes*
Affiliation:
University of Manchester
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Extract

This paper gives details of a method for measuring local heat transfer rates and shows that the results obtained are in fair agreement with the expected values.

The experiments were performed in the 8 in x 3·5 in supersonic intermittent wind tunnel at Queen Mary College (University of London). A maximum Mach number of 1·6 is obtainable at which the free stream Reynolds number in the working section is 4·92 x 106 per foot under normal conditions. The tunnel has a running time of approximately 20 seconds at a Mach number of 1·6.

The series of heat transfer measurements were restricted to flat plate conditions with non-constant wall temperatures.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 77 , Issue 746 , February 1973 , pp. 94 - 98
Copyright
Copyright © Royal Aeronautical Society 1973 

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References

1. Eckert, E. R. G. and Drake, M. R. Heat and mass transfer. McGraw-Hill Book Company Ltd, 1959.Google Scholar
2. Hughes, T. Ph.D. Thesis. University of London, 1965.Google Scholar
3. Spence, D. A. Velocity and enthalpy distribution in the compressible turbulent boundary layer on a flat plate. J. Fluid Mech. 8, 368. 1960.Google Scholar
4. Pasuick, L., Hastings, S. M. and Chatham, R. Experimental Reynolds analogy factor for a turbulent boundary layer with a pressure gradient. U.S. Naval Ordnance Laboratory, TR 64-200, 1964.Google Scholar