Hostname: page-component-7bb8b95d7b-495rp Total loading time: 0 Render date: 2024-09-15T10:23:54.006Z Has data issue: false hasContentIssue false
  • English
  • Français

Non-Linear Theory for Slender Wings in Sudden Plunging Motion

Published online by Cambridge University Press:  07 June 2016

B. D. Dore
B. D. Dore*
Affiliation:
Aerodynamics Division, National Physical Laboratory
Get access

Summary

A theoretical treatment is considered for the flow past slender wings in sudden plunging motion when leading-edge vortices are present. A form of slender-wing theory is used and, although the basis of the theory involves no restriction on compressibility, it has proved possible to make calculations only for an incompressible fluid.

Use is made of an analogy between the unsteady flow and related steady flows. In the incompressible case, an extension of the theory of Brown and Michael is given to determine the strength of the vortex and its path from the leading edge to the final steady-state position. A qualitative comparison with experiment is made of the instantaneous position of the vortex. In a typical case the lift is calculated to remain within one per cent of its final value after the vortex strength has reached 55 per cent of its final value.

Type
Research Article
Information
Aeronautical Quarterly , Volume 17 , Issue 2 , May 1966 , pp. 187 - 200
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. Lambourne, N. C., Bryer, D. W. and Maybrey, J. F. M. A preliminary note on the behaviour of the leading-edge vortices of a delta wing following a sudden change of incidence. ARC 24 187, 1962.Google Scholar
2. Dore, B. D. The unsteady motion of slender wings with leading-edge vortices. ARC CP 810, 1964.Google Scholar
3. Lowson, M. V. The separated flows on slender wings in unsteady motion. ARC 25 118, 1963.Google Scholar
4. Cheng, H. K. Aerodynamics of a rectangular plate with vortex separation in supersonic flow. Journal of the Aeronautical Sciences, Vol. 22, p. 217, April 1955.Google Scholar
5. Brown, C. E. and Michael, W. H. On slender delta wings with leading-edge separation. NACA TN 3430, 1955.Google Scholar
6. Lomax, H., Heaslet, M. A., Fuller, F. B. and Sluder, L. Two- and three-dimensional unsteady lift problems in high-speed flight. NACA Report 1077, 1952.Google Scholar
7. Smith, J. H. B. A theory of the separated flow from the curved leading edge of a slender wing. ARC R & M 3116, 1957.Google Scholar
8. Randall, D. G. Oscillating slender wings in the presence of leading-edge separation. ARC 24 929, 1963. (To be published in the Aeronautical Quarterly)Google Scholar
9. Robinson, A. and Laurmann, J. A. Wing Theory. Cambridge University Press, 1956.Google Scholar
10. Randall, D. G. A theoretical determination of the flow past and the air forces on an oscillating slender delta wing with leading-edge separation. ARC 24 910, 1963. (To be published in the Aeronautical Quarterly.)Google Scholar