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Calculation of Downwash Behind a Supersonic Wing

Published online by Cambridge University Press:  07 June 2016

G. N. Ward
G. N. Ward*
Affiliation:
Department of Mathematics, The University, Manchester
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Extract

Once the linearised lift problem for a supersonic wing has been solved and the disturbance velocity potential or the pressure is known at every point on the surface, the complete flow round the wing and the downwash behind the wing may be found by the following procedure.

Type
Research Article
Information
Aeronautical Quarterly , Volume 1 , Issue 1 , May 1949 , pp. 35 - 38
Copyright
Copyright © Royal Aeronautical Society. 1949

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References

1. Hadamard, J. (1923). Lectures on Cauchy's Problem. Yale, 1923.Google Scholar
2. Robinson, A. (1948). On Source and Vortex Distributions in the Linearised Theory of Steady Supersonic Flow. College of Aeronautics Report No. 9. A.R.C. 11132. Also Quarterly Journal of Mechanics and Applied Mathematics, 1, 4, 408, 1948.CrossRefGoogle Scholar
3. Robinson, A. and Hunter-Tod, J. H. (1947). Bound and Trailing Vortices in the Linearised Theory of Supersonic Flow and the Downwash in the Wake of a Delta Wing. College of Aeronautics Report No. 10. A.R.C. 11296, October 1947.Google Scholar
4. Robinson, A. (1946). Aerofoil Theory of a Flat Delta Wing at Supersonic Speeds. A.R.C. 10222, September 1946.Google Scholar