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Boundary Layers over Infinite Yawed Wings

Published online by Cambridge University Press:  07 June 2016

J. C. Cooke
J. C. Cooke*
Affiliation:
Royal Aircraft Establishment, Farnborough
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Summary

A method of calculating turbulent boundary layers on infinite yawed wings is given, making use of a method of calculating turbulent boundary layers due to Spence and of an analogy between three-dimensional and axi-symmetric boundary layers. It is also shown that the displacement thickness is equal to that computed using chordwise components and that the streamwise momentum thickness is approximately equal to the chordwise momentum thickness. Shock-free flow and small boundary layer cross-flow are assumed.

Type
Research Article
Information
Aeronautical Quarterly , Volume 11 , Issue 4 , November 1960 , pp. 333 - 347
Copyright
Copyright © Royal Aeronautical Society. 1960

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References

1. Rott, N. and Crabtree, L. F. Simplified Laminar Boundary-Layer Calculation for Bodies of Revolution and for Yawed Wings. Journal of the Aeronautical Sciences, Vol. 19, p. 553, 1952.CrossRefGoogle Scholar
2. Crabtree, L. F. The Compressible Laminar Boundary Layer on a Yawed Infinite Wing. The Aeronautical Quarterly, Vol. V, p. 85, 1954.CrossRefGoogle Scholar
3. Lighthill, M. J. On Displacement Thickness. Journal of Fluid Mechanics, Vol. IV, p. 383, 1958.CrossRefGoogle Scholar
4. Cooke, J. C. A Calculation Method for Three-Dimensional Turbulent Boundary Layers. A.R.C. 21059, Oct. 1958. (To be published in the R.&M. series.)Google Scholar
5. Zaat, J. A. A Simplified Method for the Calculation of Three-Dimensional Laminar Boundary Layers. N.L.L. Report F.184, April 1956.Google Scholar
6. Thwaites, B. (Editor). Incompressible Aerodynamics. Oxford University Press, 1960.CrossRefGoogle Scholar
7. Spence, D. A.The Growth of Compressible Turbulent Boundary Layers on Isothermal and Adiabatic Walls. A.R.C. 21144, June 1959. (To be published in the R.& M. series.)Google Scholar
8. Young, A. D. The Calculation of the Profile Drag of Aerofoils and Bodies of Revolution at Supersonic Speeds. College of Aeronautics Report No. 73. A.R.C. 15970. April 1953.Google Scholar
9. Cooke, J. C. An Axisymmetric Analogue for General Three-Dimensional Boundary Layers. A.R.C. 21386, June 1959. (To be published in the R.& M. series.)Google Scholar
10. Thwaites, B. Approximate Calculation of the Laminar Boundary Layer. The Aeronautical Quarterly, Vol. I, p. 245, 1949.CrossRefGoogle Scholar