The control performance of a pulsed nanosecond dielectric barrier discharge plasma actuator (NSDBD) on a supersonic compression corner at Mach 4 is investigated through numerical simulations, with a focus on evaluating the effects of varying pulse voltages, actuator locations, and pulse repetitive frequencies (PRF). The unit Reynolds number is 7.8 × 106. The plasma actuators uniformly spanwise are strategically positioned near the separation point. The simulation results demonstrate that the induced vortex caused by the discharge effectively entrains high-momentum fluid, thereby enhancing the ability to withstand adverse pressure gradients in the interaction region. Notably, it is observed that the flow separation on the supersonic compression corner can potentially be entirely eliminated. Furthermore, the plasma actuator generates a normal force that induces a pitching moment, offering the potential for controlling the body’s orientation and trajectory. Additionally, the total drag can be reduced by approximately 3.24%, indicating the potential for improved aerodynamic performance. The findings emphasize the importance of carefully selecting the actuator position based on local fluid characteristics to achieve optimal control efficiency.