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An Asymptotic Solution for the Centre of a Rolled-up Conical Vortex Sheet in Compressible Flow

Published online by Cambridge University Press:  07 June 2016

Susan N. Brown  and
K. W. Mangler
Susan N. Brown
Affiliation:
Department of Mathematics, University College, London
K. W. Mangler
Affiliation:
Royal Aircraft Establishment, Farnborough
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Summary

The asymptotic solution, valid near the centre of a rolled-up vortex sheet, obtained by Mangier and Weber, is generalised to include the effects of compressibility. The vortex sheet is taken to be embedded in a potential flow, and the flow field is assumed to be conical.

Type
Research Article
Information
Aeronautical Quarterly , Volume 18 , Issue 4 , November 1967 , pp. 354 - 366
Copyright
Copyright © Royal Aeronautical Society. 1967

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References

1. Mangler, K. W. and Weber, J. The flow field near the centre of a rolled-up conicall vortex sheet. Zeitschrift für Angewandte Mathematik und Mechanik, Sonderheft, Vol. 45, p. 165, 1965. Also RAE Tech. Report 66324, and Journal of Fluid Mechanics, Vol. 30, p. 177, 1967.CrossRefGoogle Scholar
2. Mangler, K. W. and Smith, J. H. B. A theory of the flow past a slender delta wing with leading-edge separation. Proceedings of the Royal Society (A), Vol. 251, p. 200, 1959.Google Scholar
3. Hall, M. G. A theory for the core of a leading-edge vortex. Journal of Fluid Mechanics, Vol. 11, p. 209, 1961.CrossRefGoogle Scholar
4. Mangler, K. W. and Sells, C. C. L. The flow field near the centre of a slender rolled-up conical vortex sheet. RAE Tech. Report 67029, 1967.CrossRefGoogle Scholar
5. Smith, J. H. B. Improved calculations of leading-edge separation from slender delta wings. RAE Tech. Report 66070, 1966.Google Scholar
6. Stewartson, K. and Hall, M. G. The inner viscous solution for the core of a leading-edge vortex. Journal of Fluid Mechanics, Vol. 15, p. 306, 1963.CrossRefGoogle Scholar
7. Brown, SUSAN N. The compressible inviscid leading-edge vortex. Journal of Fluid Mechanics, Vol. 22, p. 17, 1965.CrossRefGoogle Scholar
8. Michael, W. H. Flow studies on flat-plate delta wings at supersonic speed. NACA TN 3472, 1955.Google Scholar