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Some Sectional-Drag Relationships in Linearised Wing Theory

Published online by Cambridge University Press:  07 June 2016

P. R. Ashill
P. R. Ashill*
Affiliation:
Cranfield Institute of Technology
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Summary

Relationships for the sectional drag of wings are derived by using the linearised wing theory. It is suggested that some of these results may prove useful for checking the accuracy of numerical lifting-surface theories and for formulating approximate theories. Two main problems are considered, namely the lifting (no thickness) case and the thickness (zero lift) problem. In both cases, general planform shapes are examined and it is shown that particularly simple results are achieved for planar wings with a spanwise axis of symmetry.

Type
Research Article
Information
Aeronautical Quarterly , Volume 21 , Issue 4 , November 1970 , pp. 340 - 354
Copyright
Copyright © Royal Aeronautical Society. 1970

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References

1. Thwaites, B. (Editor). Incompressible aerodynamics. Clarendon Press, Oxford, 1960.Google Scholar
2. Garner, H. C., Hewitt, B. L. and Labrujere, T. E. Comparison of three methods for the evaluation of subsonic lifting-surface theory. National Physical Laboratory Aero Report 1272, 1968.Google Scholar
3. Garner, H. C. Some remarks on vortex drag and its spanwise distribution in incompressible flow. The Aeronautical Journal, Vol. 72, p. 623 July 1968.Google Scholar
4. Ashill, P. R. On some aspects of the aerodynamic performance of ground-effect wings. PhD thesis, University of Southampton, 1968.Google Scholar
5. Jones, R. T. and Cohen, D. High speed wing theory. Section A, Vol. VII of High speed aerodynamics and jet propulsion. Oxford University Press, 1957.Google Scholar
6. Robinson, A. and Laurmann, J. A. Wing theory. Cambridge University Press, 1956.Google Scholar
7. Jones, R. T. The minimum drag of thin wings in frictionless flow. Journal of the Aeronautical Sciences, Vol. 18, p. 75, 1951.Google Scholar
8. Lawrence, H. R. The lift distribution on low aspect ratio wings at subsonic speeds. Journal of the Aeronautical Sciences, Vol. 18, p. 683,1951.Google Scholar
9. Multhopp, H. Methods for calculating the lift distribution of wings (subsonic lifting-surface theory). ARC R & M 2884, 1950.Google Scholar
10. Wieghardt, K. Chordwise load distribution of a simple rectangular wing. NACA TM 963, 1940.Google Scholar
11. Küchemann, D. A simple method for calculating the span and chordwise loading on straight and swept wings of any given aspect ratio at subsonic speeds. ARC R & M 2935, 1952.Google Scholar
12. Küchemann, D. and Weber, J. The subsonic flow past swept wings at zero lift without and with body. ARC R & M 2908,1953.Google Scholar
13. Neumark, S. Critical Mach numbers for swept-back wings. Aeronautical Quarterly, Vol. II, p. 85, August 1950.Google Scholar
14. Heaslet, M. A. and Lomax, H. Supersonic and transonic small perturbation theory. Section D, Vol. VI of High speed aerodynamics and jet propulsion, Oxford University Press, 1955.Google Scholar
15. Dwight, H. B. Tables of integrals and other mathematical data. Macmillan, New York, 1961.Google Scholar