Simulations of a plunging airfoil at Re=60,000 find that 2D leading-edge actuation in a certain frequency band disrupts the stall vortex, raising suction-side pressure near the trailing edge to reduce drag while preserving lift.
Ekaterinaris, Numerical investigations of dynamic stall active control for incompressible and compressible flows, Journal of Aircraft 39, 71–78 (2002)
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Active Flow Control for Drag Reduction of a Plunging Airfoil under Deep Dynamic Stall
Simulations of a plunging airfoil at Re=60,000 find that 2D leading-edge actuation in a certain frequency band disrupts the stall vortex, raising suction-side pressure near the trailing edge to reduce drag while preserving lift.