Numerical study of leading-edge vortex control of a strake-wing at large angles of attack based on Dual Synthetic Jets

Strake wings at large angles of attack experience significant degradation in aerodynamic performance due to the leading-edge vortex breakdown phenomenon, the effective control of which, however, has yet to be thoroughly explored. This study proposes an innovative control method utilizing dual synthetic jets to delay the leading-edge vortex breakdown. The results indicate that the aerodynamic performance of a 76°/40° strake wing can be improved by installing dual synthetic jet actuators away from the sweep path of the leading-edge vortex. The proposed control method can delay the strake vortex breakdown and thereby increase the lift coefficient at a wide range of the angle of attack (AoA). For instance, the vortex breakdown is delayed by 8.4% of the chord length at AoA=40°; the lift coefficient is increased by 7.51% at AoA=35°. The reason for such a significant improvement in aerodynamic performance is the effective energy injection, achieved by an anti-phase operating manner of two jets that continuously pushes low-energy fluids to rotate in the same direction. This operation method enhances the leading-edge vortex’s capability to withstand the adverse pressure gradient, lengthens the chordwise extent of high-speed flows, and expands the area of the low-pressure zone on the leeward side, thereby increasing the vortex lifting force. The above results demonstrate the dual synthetic jets’s potential in the attitude control of slender wings.