A new concept of passive dynamic-stall control was developed and tested on an OA 209 rotorcraft airfoil during two windtunnel test campaigns in 2004 and 2005. Small vortex generators are mounted at the leading edge of the rotor blade. At low incidence they are located close to the stagnation point and do not impact the flow field. At high angles of attack the so-called leading edge vortex generators (LEVoGs) induce longitudinal vortices which impact the suction side flow. It is shown that the use of LEVoGs can significantly increase the overall time-averaged lift while an unwanted negative pitching-moment peak is reduced compared with the clean-wing case. Furthermore, overall drag is reduced at dynamic-stall conditions. Detailed analysis of the flow field by particle image velocimetry and infrared thermography show that this is achieved by a disturbance of the dynamic-stall vortex and therefore separation is partially prevented.
Dynamic stall control by leading edge vortex generators
Dynamische Regelung des Strömungsabrisses durch Wirbelgeneratoren an der Profilvorderkante
Journal of the American Helicopter Society ; 53 , 1 ; 26-36
2008
11 Seiten, 15 Bilder, 2 Tabellen, 17 Quellen
Article (Journal)
English
Dynamic Stall Control by Leading Edge Vortex Generators
Online Contents | 2008
|Dynamic Stall Control by Leading Edge Vortex Generators
British Library Conference Proceedings | 2006
|Dynamic stall control by leading edge vortex generators
Tema Archive | 2006
|Experimental Study of Dynamic Stall Control Using Deployable Leading-Edge Vortex Generators
British Library Conference Proceedings | 2011
|