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The Lift of Twisted and Cambered Wings in Supersonic Flow*

Published online by Cambridge University Press:  07 June 2016

G. N. Lance
G. N. Lance*
Affiliation:
Department of Engineering, University of California
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Summary

A generalised conical flow theory is used to deduce an integral equation relating the velocity potential on a delta wing (with subsonic leading edges) to the given downwash distribution over the wing. The complete solution of this integral equation is derived. This complete solution is composed of two parts, one being symmetric and the other anti-symmetric with respect to the span wise co-ordinate; each part represents a velocity potential. For example, if y is the spanwise co-ordinate and x is measured in the free stream direction, then a downwash of the form w= - α11 Ux|y| is symmetric and will give rise to a symmetric potential, whereas w= - α11 Ux|y| sgn y is anti-symmetric and gives rise to an anti-symmetric potential. The velocity potentials of such flows are given in the form of Tables for all downwashes up to and including homogenous cubics in the spanwise and streamwise co-ordinates. Table III gives similar formulae in the limiting case when the leading edges become transonic; these are compared with results given elsewhere and serve as a check on the results of Tables I and II.

Type
Research Article
Information
Aeronautical Quarterly , Volume 6 , Issue 2 , May 1955 , pp. 149 - 163
Copyright
Copyright © Royal Aeronautical Society. 1955

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Footnotes

*

This work was carried out under the auspices of the F.O.A. Scientific Research Project TA 01-101-3006 (OEEC 151).

References

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