A numerical simulation method of rotor dynamic stall control based on synthetic jet is developed to solve the dynamic stall caused by coupling of flow velocity and angle of attack(AoA). This method is realized by the translation and rotation of the two-dimensional airfoil. Reynolds N-S equation in integral form is taken as the main control equation. Roeformat is used for spatial discrealization and implicit LU-SGS method for temporal discrealization. Taking the OA209 airfoil as the object, the synthetic jet excimer is placed on the upper surface of the airfoil, and the study on the dynamic stall control of airfoil with slight and deep stall is carried out with the parameters of jet position, momentum coefficient, dimensionless frequency and angle. It is found that under slight stall, when the jet position is close to the flow separation point (around 20%c), the control effect of slight stall caused by adverse pressure gradient is the best. Although the separation point of airflow under deep stall is before 5% c, the control effect is better when the jet is located behind the leading edge separation bubble (near 10% c). High angle of attack requires large momentum coefficient. The frequency has a certain influence on the size and number of vortexes and changes the fluctuation range of aerodynamic characteristics. Small angle of jet is more effective to control slight stall, while deep stall requires large angle.