Abstract: In order to study the control effect and mechanism of AC-DBD plasma actuators on NACA0012 airfoil, dynamic pressure measurement and PIV measurement were used in research of dynamic stall control over pitching and coupled motion. The results show that the plasma actuators can significantly delay the stall angle of attack, suppress the sharp drop of lift coefficient, advance the flow reattachment and lift coefficient recovery, reduce the hysteresis loop area of lift and pitch moment coefficient circles and improve the aerodynamic characteristics of airfoil. The influence of different motion parameters and actuator setting parameters on the control effect was studied. The results show that the frequencies of airfoil motion and actuator excitation have the greatest impact on the actuator control effect, respectively. This work also provides a data basis for the following related research.