Hostname: page-component-848d4c4894-p2v8j Total loading time: 0.001 Render date: 2024-05-16T04:34:29.804Z Has data issue: false hasContentIssue false
  • English
  • Français

Supersonic Flow Past Slender Pointed Wings with “Similar” Cross Sections at Zero Lift

Published online by Cambridge University Press:  07 June 2016

W. T. Lord  and
G. G. Brebner
W. T. Lord
Affiliation:
Royal Aircraft Establishment, Farnborough
G. G. Brebner
Affiliation:
Royal Aircraft Establishment, Bedford
Get access

Summary

Some recent theoretical work on slender pointed wings at zero lift is co-ordinated and extended. The wings considered may have any pointed plan form shape, provided that the trailing edge is straight and unswept. The root section profile and cross-section shapes are arbitrary, provided that, on any one wing, the latter are “descriptively similar” (diamond or parabolic biconvex for instance), though not necessarily geometrically similar. The chief aim of the work is to find wings with simple geometry, low wave drag and pressure distributions which are unlikely to be seriously affected by viscous effects. Wave drag and pressure distributions are calculated by slender-wing theory. General formulae, which are both simple and instructive, are given for the wave drag and the overall pressure distribution, with particular emphasis on the root pressure distribution. Results for a number of wings of special interest are presented and discussed.

Type
Research Article
Information
Aeronautical Quarterly , Volume 10 , Issue 1 , February 1959 , pp. 79 - 102
Copyright
Copyright © Royal Aeronautical Society. 1959

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. Weber, J. Slender Delta Wings with Sharp Edges at Zero Lift. R.A.E. Technical Note Aero 2508.Google Scholar
2. Lord, W. T. and Green, B. Some Thickness Distributions for Narrow Wings. R.A.E. Technical Note Aero 2495.Google Scholar
3. Weber, J. The Pressure Distribution over a “Gothic” Wing at Zero Lift in Supersonic Flow. R.A.E. Technical Note Aero 2490.Google Scholar
4. Maskell, E. C. and Weber, J. On the Aerodynamic Design of Slender Wings. Unpublished R.A.E. paper.Google Scholar
5. Fraenkel, L. E. Supersonic Flow past Slender Bodies of Elliptic Cross-Section. R. & M. 2954.Google Scholar
6. Stocker, P. M. Supersonic Flow past Bodies of Revolution with Thin Wings of Small Aspect Ratio. Aeronautical Quarterly, Vol. III, May 1951.Google Scholar
7. Lord, W. T. Supersonic Flow past a Particular Type of Slender Wing-Body Combination at Zero Incidence. R.A.E. Technical Note Aero 2134.Google Scholar
8. Heaslet, M. A. and Lomax, H. The Calculation of Pressure on Slender Airplanes in Subsonic and Supersonic Flow. N.A.C.A. Report 1185.Google Scholar
9. Byrd, P. F. Theoretical Pressure Distributions for Some Slender Wing-Body Combinations at Zero Lift. N.A.C.A. R.M. A54J07.Google Scholar
10. Ward, G. N. The Supersonic Flow past a Slender Ducted Body of Revolution with an Annular Intake. Aeronautical Quarterly, Vol. I, February 1950.Google Scholar
11. Fraenkel, L. E. and Portnoy, H. Supersonic Flow past Slender Bodies with Discontinuous Profile Slope. Aeronautical Quarterly, Vol. VI, May 1955.Google Scholar
12. Lighthill, M. J. The Wave Drag at Zero Lift of Slender Delta Wings and Similar Configurations. Journal of Fluid Mechanics, Vol. I, Part 3, September 1956.Google Scholar
13. Newby, K. W. The Effects of Taper on the Supervelocities on Three-Dimensional Wings at Zero Incidence. R.& M. 3032.Google Scholar
14. Peckham, D. H. and Atkinson, S. A. Preliminary Results of Low Speed Wind Tunnel Tests on a “Gothic” Wing of Aspect Ratio 10. R.A.E. Technical Note Aero 2504.Google Scholar