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Notes on the Linear Theory of Incompressible Flow Round Symmetrical Swept-Back Wings at Zero Lift

Published online by Cambridge University Press:  07 June 2016

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

In much of the recent work on the flow of an incompressible fluid past a swept-back symmetrical wing of small thickness at zero incidence it has been assumed that the disturbance introduced by the wing can be represented by means of a distribution of sources and sinks over the centre plane of the wing, the source strength being determined from the equation of the wing profile. It was found by Neumark that on the wing itself this procedure was liable to lead to serious errors. Neumark and Kuchemann studied certain special types of wings for which they were able to find the correct value of the pressure at the surface by evaluation of the pressure at points off the wing and continuity considerations. This process is rather cumbersome; it may therefore be convenient to regard the problem from a rather different point of view.

Type
Research Article
Information
Aeronautical Quarterly , Volume 1 , Issue 1 , May 1949 , pp. 101 - 122
Copyright
Copyright © Royal Aeronautical Society. 1949

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References

1. Neumark, S. (1947). Velocity Distribution on Straight and Swept-Back Wings of Small Thickness and Infinite Aspect Ratio at Zero Incidence. R.A.E. Report No. Aero 2200. A.R.C. 10907, May 1947.Google Scholar
2. Küchemann, D. (1947). Wing Junction, Fuselage and Nacelles for Swept-Back Wings. R.A.E. Report No. Aero 2219. A.R.C. 11035, August 1947.Google Scholar
3. Ludwieg, H. (1946). Improvement on the Critical Mach Number of Aerofoils by Sweep-Back. M.A.P. Völkenrode. Reports and Translations. No. 84. A.R.C. 9826, July 1946.Google Scholar
4. Carleman, T. (1922). Sur la Résolution de Certaines Equations Intégrates. Arkiv. för Mat. Astron. och Fysik, 16, Nr. 26, 1922.Google Scholar