This study investigates the aerodynamic performance of the NACA 633-421 airfoil and the effectiveness and feasibility of intermittent disturbance flow control methods on laminar separation bubbles （LSBs）. It is found that the average velocity and influence range of the synthetic jet actuator increase with the increasing of driving frequency and driving amplitude. LSB occurs at Re=1.0×10⁵， and ruptures at α=6°. But with intermittent disturbance control， the stall angle of attack （AoA） increases while significantly reducing drag. Research shows that although certain disturbance cannot fully recover from LSB stall， decreasing driving amplitude partially restores wing aerodynamic performance， more effectively than increasing driving amplitude.