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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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