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Correlation of Total Lift Data for Thin, Sharp-Edged, Low-Aspect-Ratio Delta Wings at Low Speeds

Published online by Cambridge University Press:  04 July 2016

A. J. Alexander
A. J. Alexander*
Affiliation:
Dept. of Mechanical Engineering, The University of Technology, Loughborough.
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Extract

The amount of research carried out in the field of highly swept wings has reached massive proportions. No attempt is made to review the literature on this subject but it seems that despite all efforts, no method yet exists for calculating the lift of delta wings in subsonic flow where the trailing-edge condition makes true conical flow impossible. A recent paper by Nangia and Hancock, has attempted this very difficult problem but the method proposed is not yet suitable for general application. Greater success has been obtained in supersonic flow,see for example ref.2.

Various formulae have been obtained for the lift coefficient of delta wings in conical flow and the lift can be divided into two parts; the linear part where the flow is fully attached in the region of zero incidence and the nonlinear part where extra lift is obtained from the leading edge vortices. One typical formula is derived from a relatively simple theory by Edwards.

Type
Technical Notes
Information
The Aeronautical Journal , Volume 75 , Issue 728 , August 1971 , pp. 569 - 570
Copyright
Copyright © Royal Aeronautical Society 1971 

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References

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