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Some Practical Aspects of Kinetic Heating Calculations

Published online by Cambridge University Press:  04 July 2016

C. L. Bore
C. L. Bore*
Affiliation:
Project Office, Hawker Aircraft Ltd.
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Extract

This paper is concerned primarily with some of the practical difficulties encountered in connection with the prediction of kinetic heating temperatures. Attention will be concentrated upon methods for estimating temperatures and heat transfer rates for practical aircraft designed to fly at Mach numbers up to about five.

One factor common to all kinetic heating calculations is the variation of temperature through the thickness of the boundary layer, with consequent variation of viscosity. At Mach numbers above about 3, these temperature variations also lead to considerable variations of other properties of air—which are commonly assumed to remain constant—even in classical compressible flow aerodynamics. These factors complicate the aerodynamic equations.

Type
The Structural Effects of Kinetic Heating
Information
The Aeronautical Journal , Volume 63 , Issue 587 , November 1959 , pp. 637 - 645
Copyright
Copyright © Royal Aeronautical Society 1959

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References

1.Eckert, R. G. (1954). Survey on Heat Transfer at High Speeds. W.A.D.C. Technical Report 54-70. April 1954.Google Scholar
2.Monaghan, R. J. (1955). On the Behaviour of Boundary Layers at Supersonic Speeds. Proceedings of the Fifth Anglo-American Aeronautical Conference, Los Angeles, 1955. Institute of the Aeronautical Sciences, 1955.Google Scholar
3.Monaghan, R. J. (1955). Formulae and Approximations for Aerodynamic Heating Rates in High Speed Flight. Unpublished Ministry of Supply Report, Oct. 1955.Google Scholar