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Some Aspects of Laminar Boundary Layer Separation in Compressible Flow with no Heat Transfer to the Wall

Published online by Cambridge University Press:  07 June 2016

G. E. Gadd
G. E. Gadd*
Affiliation:
Beit Scientific Research Fellow
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Summary

An analysis has been made which suggests that, with the types of pressure distribution most usual in practice and free stream Mach numbers up to 10, no serious errors would be introduced into the calculation of the laminar separation point by the assumption that σ, the Prandtl number, and ω, the index of variation of viscosity with absolute temperature, are equal to unity. (Typical actual values of σ and ω for air are 0.72 and 0.89 respectively).

Type
Research Article
Information
Aeronautical Quarterly , Volume 4 , Issue 2 , August 1953 , pp. 123 - 150
Copyright
Copyright © Royal Aeronautical Society. 1953

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References

1. Young, A. D. (1949). Skin Friction in Compressible Flow. The Aeronautical Quarterly, Vol. 1, August 1949.Google Scholar
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3. Illingworth, C. R. (1949). Steady Flow in the Laminar Boundary Layer of a Gas. Proc. Roy. Soc. A. 199, p. 533, 1949.Google Scholar
4. Crocco, L. (1939). A Characteristic Transformation of the Equations of the Boundary Layer in Gases. A.R.C. 4582, 1940.Google Scholar
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6. Thwaites, B. (1949). Approximate Calculation of the Laminar Boundary Layer. The Aeronautical Quarterly, Vol. 1, November 1949.CrossRefGoogle Scholar