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Note on the Drag Due to Lift of Slender Wings

Published online by Cambridge University Press:  28 July 2016

D. Küchemann
D. Küchemann*
Affiliation:
Royal AiYcraft Establishment,Farnborough
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Extract

Several Attempts have been made lately to reduce the drag due to lift of wings by means of camber and twist. Slender wings in particular have been considered and a typical theory is that by Tsien on the supersonic conical wing of minimum drag, where the lift forces on the wing are calculated from conventional aerofoil theory so that the overall lift of a flat wing turns out to be proportional to the angle of incidence. For convenience, this is called a “ linear theory.” It is usual to consider two cases: (1) Wings where the drag is calculated by the same theory so that the full thrust component and the suction at the leading edge are included. (2) Wings where the drag is not calculated by the same theory as the lift but where the thrust at the leading edge is omitted.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 61 , Issue 558 , June 1957 , pp. 423 - 424
Copyright
Copyright © Royal Aeronautical Society 1957

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References

1. Tsien, H. S. (1955). The Supersonic Conical Wing of Minimum Drag. Journal of the Aeronautical Sciences, Vol. 22, p. 805, December 1955.Google Scholar
2. Jones, R. T. (1946). Properties of Low-Aspect-Ratio Pointed Wings at Speeds Below and Above the Speed of Sound. N.A.C.A. Report No. 835, 1946.Google Scholar
3. Küchemann, D. A Non-Linear Lifting-Surface Theory for Wings of Small Aspect Ratio with Edge Separations. Unpublished M.O.S. Report.Google Scholar