Abstract: Numerical methods are adopted to investigate the flow field of zero net mass flux actuator, including the supersonic inlet flow field with actuator. The Roe upwind scheme and the fully implicit dual-time step method are utilized for spatial discretization and time marching respectively. The parallelized deforming grid algorithm based on transfinite interpolation is used to simulate the unsteady flow fields with moving boundaries, considering the geometric conservation law. The influence of driving frequency on zero net mass flux actuator is analyzed to study the unsteady characteristics of zero net mass flux. Furthermore, the different effects of flow control by zero net mass flux flow actuator in supersonic inlet flow field are derived using different driving frequencies. The results show that numerical methods are suitable to represent zero net mass flux and the actuator can effectively improve the supersonic performance.