Abstract: The leading-edge vortex rupture phenomenon occurs in stake-wing at large head-on angles, and the aerodynamic performance is significantly degraded. To solve this problem, a vortex rupture control method based on Dual Synthetic Jets is proposed in this study. Dual Synthetic Jets actuators are installed on the outside of the edge vortex sweep path of the 76°/40° strake-wing, which effectively influences the flow development of the edge vortex and improves the aerodynamic characteristics of the aircraft. The results show that the application of the control delays the rupture point of the sidebar vortex at each head-on angle at a free incoming Mach number of 0.1, and the vortex breakdown delay reaches 8.4% of chord length at 40° angle of attack; meanwhile, the lift coefficient is significantly improved, and the maximum lift increment reaches 7.51% at 35° angle of attack. The two jets of the Dual Synthetic Jets actuators act in an anti-phase manner to continuously push the low-energy airflow to rotate in the same direction, which achieves the effective injection of energy, enhances the ability of the sidebar vortex to resist the counterpressure gradient, and lengthens the flow distance of the high-velocity flow, thus enlarging the area of low-pressure zone on the leeward side, and increasing the vortex lifting force. The Dual Synthetic Jets is effective in controlling the aerodynamic forces and vortex rupture phenomenon of the strake-wing, showing its great potential in the attitude control of slender wings.