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A Note on Supersonic Wing Integral Equations in Unsteady Flow*

Published online by Cambridge University Press:  07 June 2016

John W. Miles
John W. Miles*
Affiliation:
Auckland University College, New Zealand. On leave from the University of California, Los Angeles
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Summary

The integral equations for the pressure distribution on an oscillating thin wing having a prescribed velocity distribution in a supersonic flow are developed.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 3 , Issue 4 , February 1952, pp. 294 - 296
Copyright
Copyright © Royal Aeronautical Society. 1952

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Footnotes

*

This work was done in 1948, at which time it was hoped to extend the very elegant methods available for the steady flow problem. All attempts to generalise these methods for wings of arbitrary plan form having proved nugatory, it is felt that the integral equations are worth recording.

References

1. Garrick, I. E. and Rubinow, S. I. (1947). Theoretical Study of Air Forces on an Oscillating or Steady Thin Wing in a Supersonic Main Stream. N.A.C.A. T.N. 1383, 1947.Google Scholar
2. Miles, J. W. (1951). The Oscillating Rectangular Airfoil at Supersonic Speeds. Quarterly of Applied Mathematics, Vol. IX, pp. 47–65, 1951.Google Scholar
3. Fox, E. N. (1948). The Diffraction of Sound Pulses by an Infinitely Long Strip. Phil. Trans. Roy. Soc, A, Vol. 241, pp. 7–103, 1948.Google Scholar
4. Stewartson, K. (1950). On the Linearised Potential Theory of Unsteady Supersonic Motion. Quarterly Journal of Mechanics and Applied Mathematics, Vol. Ill, pp. 182–199, 1950.Google Scholar