Abstract A back-flow flap attached to the suction side of an airfoil is investigated in both passively and actively actuated modes for the control of dynamic stall. This method of dynamic stall control has low power requirements and no parasitic drag when not actuated. Experiments in a low-speed wind tunnel at 50 m/s were used to characterize the reduction in dynamic stall hysteresis using pressure measurements on the midline airfoil section. It was found that the pitching moment peak is reduced by an average of 25% for all deep stall test cases for active actuation of the flap, while for passive actuation the pitching moment peak is reduced by 19%. In each case the maximum lift remained the same, while the peak drag increased by an average of 2.5% for the active flap, and by 0.9% for the passive flap. With the flap closed at low angles of attack, the reference values of the airfoil are retained.
Reduction of dynamic stall using a back-flow flap
CEAS Aeronautical Journal ; 8 , 2 ; 271-286
2017-02-17
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Reduction of dynamic stall using a back-flow flap
Online Contents | 2017
|Influence of a back-flow flap on the dynamic stall flow topology
Springer Verlag | 2017
|Influence of a back-flow flap on the dynamic stall flow topology
Online Contents | 2017
|Trailing-edge flap flow control for dynamic stall
Online Contents | 2011
|Trailing Edge Flap Flow Control for Dynamic Stall
British Library Conference Proceedings | 2010
|