Abstract
Numerical investigations with the DLR TAU Code demonstrate that an actuated back-flow flap on the suction side of an OA209 helicopter airfoil is able to improve the dynamic stall behavior. When the flow begins to stall, the flap is extended which interferes with the back-flow. This weakens the dynamic stall vortex and consequently the peak in the pitching moment peak is reduced.
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Kaufmann, K., Gardner, A.D., Richter, K. (2014). Numerical Investigations of a Back-Flow Flap for Dynamic Stall Control. In: Dillmann, A., Heller, G., Krämer, E., Kreplin, HP., Nitsche, W., Rist, U. (eds) New Results in Numerical and Experimental Fluid Mechanics IX. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 124. Springer, Cham. https://doi.org/10.1007/978-3-319-03158-3_26
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DOI: https://doi.org/10.1007/978-3-319-03158-3_26
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