Hostname: page-component-586b7cd67f-vdxz6 Total loading time: 0 Render date: 2024-11-28T09:58:54.241Z Has data issue: false hasContentIssue false
  • English
  • Français

Oscillating Slender Wings with Leading-Edge Separation

Published online by Cambridge University Press:  07 June 2016

D. G. Randall
D. G. Randall*
Affiliation:
Royal Aircraft Establishment, Farnborough
Get access

Summary

A theoretical study is made of the aerodynamics of wings executing simple harmonic oscillations. The wings considered are slender and infinite-simally thin; they may have curved leading edges and be cambered, but their cross sections must be straight lines. The value of the reduced frequency is assumed to be such that the flow is governed by the two-dimensional Laplace equation.

Leading-edge separation is simulated by a line vortex joined to the leading edge by a cut. The strength and position of the vortex and the values of the generalised forces can be determined by the theory. Results have been calculated for flat delta wings and a flat gothic wing; they are in reasonable agreement with experiment.

Type
Research Article
Information
Aeronautical Quarterly , Volume 17 , Issue 4 , November 1966 , pp. 311 - 331
Copyright
Copyright © Royal Aeronautical Society. 1966

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. Brown, C. E. and Michael, W. H. On slender delta wings with leading-edge separation. NACA TN 3430, April 1955.Google Scholar
2. Smith, J. H. B. A theory of the separated flow from the leading edge of a slender wing. R & M 3116, 1959.Google Scholar
3. Robinson, A. and Laurmann, J. A. Wing theory. Cambridge University Press, 1956.Google Scholar
4. Lowson, M. V. The separated flows on slender wings in unsteady motion. ARC 25 118, September 1963.Google Scholar
5. Miles, J. W. The potential theory of unsteady supersonic flow. Cambridge University Press, 1959.Google Scholar
6. Hancock, G. J. Transient motion of a slender delta wing with leading edge separation. ARC 21 754, 1960.Google Scholar
7. Wright, J. G. Low speed wind tunnel measurements of the oscillatory longitudinal derivatives of a gothic wing of aspect ratio 0·75. Bristol Aircraft Company, Report W.T. 368, September 1961.Google Scholar
8. Lambourne, N. C. and Bryer, D. W. Measured positions of the leading edge vortices of a delta wing oscillating in pitch. National Physical Laboratory Aero Report (unpublished), superseding ARC 21 844.Google Scholar
9. Maltby, R. L., Enoler, P. B. and Keating, R. F. A. Some exploratory measurements of leading-edge vortex positions on a delta wing oscillating in heave. RAE Tech Note Aero 2903, July 1963.Google Scholar
10. Moss, G. F. Further analysis of measurements of leading edge vortex position on a delta wing oscillating in heave. RAE Tech Note Aero 2903A, September 1964.Google Scholar
11. Randall, D. G. RAE unpublished Tech Memo.Google Scholar
12. Mangler, K. W. and Smith, J. H. B. A theory of the flow past a slender delta wing with leading edge separation. Proc. Roy. Soc. A, Vol. 251, p. 200, 1959.Google Scholar
13. Garner, H. C. and Lehrian, D. E. Pitching derivatives for a gothic wing oscillating about a mean incidence. ARC Current Paper 695, 1963.Google Scholar