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Transition and separation control in the leading edge region

Published online by Cambridge University Press:  04 July 2016

P. W. C. Wong ,
M. Maina  and
A. M. Cobbin
P. W. C. Wong
Affiliation:
Aircraft Research Association , Manton Lane, Bedford, UK
M. Maina
Affiliation:
Aircraft Research Association , Manton Lane, Bedford, UK
A. M. Cobbin
Affiliation:
Aircraft Research Association , Manton Lane, Bedford, UK
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Abstract

This paper describes an investigation of methods of controlling transition and separation in the leading edge region of military aircraft wings. For wings with the high leading edge sweep relevant to some military aircraft, if attachment line contamination can be prevented then transition is predominantly caused by crossflow instability close to the leading edge. The use of surface suction or cooling for suppressing these instabilities in order to delay transition, has been investigated in a parametric study. The placing of a short suction panel close to the leading edge has been found to be an effective means of controlling instability. Conversely, the level of cooling required to suppress crossflow instability may be too high for practical aircraft applications. The use of suction for preventing laminar separation for pressure distributions with a leading edge suction peak has also been included in the parametric study. The suction quantity required is strongly dependent on the peak height. The suction quantity that can be achieved in practice will limit the maximum peak height that can be attained without laminar separation. An investigation of leading edge stall and control has also been carried out. The analysis suggests that it is important to be able to identify whether the stall is due to laminar bubble bursting or turbulent re-separation, since different methods of controlling the stall may be required.

Type
Research Article
Information
The Aeronautical Journal , Volume 105 , Issue 1049 , July 2001 , pp. 371 - 378
Copyright
Copyright © Royal Aeronautical Society 2001 

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References

1. Poll, D.I.A. and Paisley, D.J. On the effect of wing taper and sweep direction on leading edge transition, Aeronaut J, March 1985, 89, (883), pp 109–117.Google Scholar
2. Wong, P.W.C. and Maina, M. An investigation of hybrid laminar flow aerofoil pressures distributions and performance characteristics, 2nd European Forum on Laminar Flow Technology, June 1996.Google Scholar
3. Atkin, C.J. Unpublished work at BAe Regional Aircraft.Google Scholar
4. Ashill, P.R., Betts, C.J. and Gaudet, I.M. A wind tunnel study of transition flows on a swept panel wing at high subsonic speeds, 2nd European Forum on Laminar Flow Technology, June 1996.Google Scholar
5. Brown, S.M. Unpublished work at BAe Commercial Aircraft.Google Scholar
6. Evans, W.T. and Mort, K.W. Analysis of computed flow parameters for a set of sudden stalls in low-speed two dimensional flow, NACA TN D-85, August 1959.Google Scholar
7. van den berg, B. Role of laminar separation bubbles in airfoil leading edge stalls, AIAA 81-4104, May 1981.Google Scholar
8. Horton, H.P. A semi-empirical theory for the growth and bursting of laminar separation bubbles, ARC Report 29185,1967.Google Scholar
9. Gaster, M. The structure and behaviour of laminar separation bubbles, AGARD CP 4, 1966, pp 819–854.Google Scholar
10. Ashill, P.R., Wood, R.F. and Weeks, D.J. An improved, semi-inverse version of the viscous Garabedian and Korn method (VGK), RAE TR 87002, 1987.Google Scholar
11. Mccullough, G.B. and Gault, D.E. Examples of three representative types of airfoil-section stall at low speed, NACA TN 2502, 1951.Google Scholar
12. Roberts, W.B. Calculation of laminar separation bubbles and their effect on airfoil performance, AIAA J, January 1980, 18, (1).Google Scholar
13. Haines, A.B. Scale effects on aircraft and weapon aerodynamics, AGARD-AG-323, July 1994.Google Scholar