Hostname: page-component-77c89778f8-sh8wx Total loading time: 0 Render date: 2024-07-18T04:28:25.629Z Has data issue: false hasContentIssue false
  • English
  • Français

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.
Get access Rights & Permissions [Opens in a new window]

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 

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

1. Nangia, R. K. and Hancock, G. J. A theoretical investigation for delta wings with leading edge separation at low speeds. ARC Paper 30 608 August, 1968.Google Scholar
2. Squire, L. C. The estimation of the non-linear lift of delta wings at supersonic speeds. Journal of the Royal Aeronautical Society, Vol 67, No 632, pp. 476–480, AugustGoogle Scholar
3. Edwards, R. H. Leading edge separation from delta wings. Journal of Aeronautical Sciences, Vol 21, No 2, p. 134, February 1954.Google Scholar
4. Mangler, K. and Smith, J. H. B. A theory of the flow past a delta wing with leading edge separations. Proc Roy Soc, Vol 251, pp. 200–217, 1959.Google Scholar
5. Flax, A. H. and Lawrence, H. R. The aerodynamics of low aspect ratio wings and wing body combinations. Third Anglo-American Aeronautical Conference 1951.Google Scholar
6. Küchemann, D. Aircraft shapes and their aerodynamics for flight at supersonic speeds. Advances in Aeronautical Sciences, Vol 3, Pergamon Press, 1962.Google Scholar
7. Peckham, D. H. LOW speed wind tunnel tests on a series of uncambered pointed wings with sharp edges. ARC Rep. and Mem. 3186, 1961.Google Scholar
8. Kirby, D. A. An experimental investigation of the effect of planform shape on the subsonic longitudinal stability characteristics of slender wings. ARC Rep. and Mem. 3568, 1969.Google Scholar
9. Hummel, D. and Srinivasan, P. S. Vortex breakdown effects on the low speed aerodynamic characteristics of slender delta wings in symmetrical flow. Journal of the Royal Aeronautical Society, Vol 71, No 676, pp. 319–322, April 1967.Google Scholar
10. Bartlett, G. E. and Vidal, R. J. Experimental investigation of influence of edge shape on the aerodynamic characteristics of low aspect ratio wings at low speeds. Journal of Aeronautical Sciences, Vol 22, No 8, pp. 517–533, August 1955.Google Scholar
11. Squire, L. C. Camber effects on the non-linear lift of slender wings with sharp leading edges. ARC Current Paper 924, 1967.Google Scholar
12. Betz, A. “Applied Aerofoil Theory”, Aerodynamic Theory. Durand, Vol IV, pp. 69–72, 1943.Google Scholar