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Mass Transfer Cooling in a Boundary Layer

Published online by Cambridge University Press:  07 June 2016

D. G. Hurley
D. G. Hurley*
Affiliation:
Aeronautical Research Laboratories, Australian Defence Scientific Service
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Summary

Previous theoretical work on mass transfer cooling is reviewed and it is shown that this may be complemented by similar solutions that occur when the velocity outside a two-dimensional boundary layer varies as some power of the distance from the front stagnation point. The case of stagnation point flow with constant wall temperature is investigated in some detail, under the assumption that the temperature differences are everywhere small compared with the absolute temperature. Calculations on an analogue computer, supplemented by an investigation of the asymptotic behaviour, are used to determine the boundary layer development and heat transfer rates when the coolant is hydrogen, helium, steam or carbon dioxide. It is found that, on a mass flow basis, hydrogen reduces the heat transfer rate most and that steam is the next most effective of the substances investigated.

Type
Research Article
Information
Aeronautical Quarterly , Volume 12 , Issue 2 , May 1961 , pp. 165 - 188
Copyright
Copyright © Royal Aeronautical Society. 1961

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References

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