Hostname: page-component-cd9895bd7-gbm5v Total loading time: 0 Render date: 2024-12-28T05:31:22.356Z Has data issue: false hasContentIssue false
  • English
  • Français

Separated Flow Past a Slender Delta Wing at Incidence

Published online by Cambridge University Press:  07 June 2016

J E Barsby
J E Barsby*
Affiliation:
University of East Anglia, Norwich
Get access

Summary

Solutions to the problem of separated flow past slender delta wings for moderate values of a suitably defined incidence parameter have been calculated by Smith, using a vortex sheet model. By increasing the accuracy of the finite-difference technique, and by replacing Smith’s original nested iteration procedure, to solve the non-linear simultaneous equations that arise, by a Newton’s method, it is possible to extend the range of the incidence parameter over which solutions can be obtained. Furthermore for sufficiently small values of the incidence parameter, new and unexpected results in the form of vortex systems that originate inboard from the leading edge have been discovered. These new solutions are the only solutions, to the author’s knowledge, of a vortex sheet leaving a smooth surface.

Interest has centred upon the shape of the finite vortex sheet, the position of the isolated vortex, and the lift, and variations of these quantities are shown as functions of the incidence parameter. Although no experimental evidence is available, comparisons are made with the simpler Brown and Michael model in which all the vorticity is assumed to be concentrated onto an isolated line vortex. Agreement between these two models becomes very close as the value of the incidence parameter is reduced.

Type
Research Article
Information
Aeronautical Quarterly , Volume 24 , Issue 2 , May 1973 , pp. 120 - 128
Copyright
Copyright © Royal Aeronautical Society. 1973

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 Smith, J H B Improved calculations of leading-edge separation from slender delta wings. RAE Technical Report 66070, 1966; Proc Roy Soc A, Vol 306, pp 67-90, 1968.Google Scholar
2 Barsby, J E Separated flow past slender wings with camber. RAE Technical Report 72179, 1972.Google Scholar
3 Pullin, D I Calculations of the steady conical flow past a yawed slender delta wing with leading-edge separation. 1C Aero Report 72-17, Imperical College, London, July 1972.Google Scholar
4 Brown, C E Michael, W H On slender delta wings with leading-edge separation. NACA TN 3430, April 1955; Journal of the Aerospace Sciences, Vol 21, pp 690-694 and 706, 1954.Google Scholar
5 Smith, J H B Remarks on the structure of conical flow. Chapter 4, Progress in Aeronautical Science, Vol 12, edited by Küchemann, D, Pergamon Press, 1972.Google Scholar
6 Edwards, R H Leading-edge separation from delta wings. Journal of the Aerospace Sciences, Vol 21, pp 134-135, 1954.Google Scholar