Effects of plasma actuator on the dynamically stalled flowfield with Re = 2.56 × 10~5 around a pitching NACA0012 airfoil have been investigated by large-eddy simulations (LESs) with sufficient computational spanwise domain length. The dynamically stalled flowfield is characterized by laminar separation bubble, dynamic stall vortex and fully separated flowfield and the current LESs show good agreements with the experimental results with and without plasma actuator. With plasma actuator, the lift coefficient C_L during the pitching down is significantly enhanced by the induced large leading edge vortex, whereas the drag coefficient C_D is also increased.
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