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Supersonic Flow over Thin Symmetrical Wings with Given Surface Pressure Distribution

Published online by Cambridge University Press:  07 June 2016

F. A. Goldsworthy
F. A. Goldsworthy*
Affiliation:
Department of Mathematics, The University, Manchester
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Summary

The inverse problem of determining the supersonic flow past a thin symmetrical wing at zero incidence with given surface pressure distribution is solved for wings of arbitrary plan form. Expressions are obtained for the vertical derivative of the potential on the wing surface from which, using the linearised boundary condition of zero normal velocity at the surface, the profile of the wing can be designed. The integral equation method adopted by J. C. Evvard and extended by G. N. Ward is used. The analysis cannot be applied to pointed wings, whose leading edges are subsonic. The results in Part I are completely general and are applied to specific problems in Part II.

Type
Research Article
Information
Aeronautical Quarterly , Volume 3 , Issue 4 , February 1952 , pp. 263 - 279
Copyright
Copyright © Royal Aeronautical Society. 1952

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References

1. Puckett, A. E. (1946). Supersonic Wave Drag of Thin Airfoils. Journal of the Aeronautical Sciences, Vol. 13, pp. 475–484, 1946.CrossRefGoogle Scholar
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3. Ward, G. N. (1949). Supersonic Flow Past Thin Wings. Quarterly Journal of Mechanics and Applied Mathematics, Vol. II, pp. 136–152, 1949.CrossRefGoogle Scholar
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