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The Compressible Laminar Boundary Layer on a Yawed Infinite Wing*

Published online by Cambridge University Press:  07 June 2016

L. F. Crabtree
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Summary

A study of the laminar boundary layer on a yawed infinite wing in a compressible fluid is made. A method is presented for the investigation of compressibility effects by direct solution of the linearised equations of motion, first considerably simplified by the extension of a transformation due to Illingworth and Stewartson, which assumes a heat-insulated surface and a fluid of unit Prandtl number and a coefficient of viscosity which is proportional to the absolute temperature. As an example of this procedure the boundary layer near a stagnation point is calculated. The simplifications necessary for an extension of the momentum method, which is available for a yawed infinite wing in an incompressible fluid, are discussed, and this method is recommended for a first evaluation of the effect of compressibility.

Type
Research Article
Information
Aeronautical Quarterly , Volume 5 , Issue 2 , July 1954 , pp. 85 - 100
Copyright
Copyright © Royal Aeronautical Society. 1954

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Footnotes

*

Based on part of a thesis presented in partial fulfilment of the requirements for the degree of Ph.D., Cornell University.

References

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