Abstract: Fluid separation on the surface of supersonic projectiles and missiles is one of the main factors influencing their flight stability. Studies have shown that micro-wedge vortex generators (MVG) can effectively control the flow separation of the supersonic boundary layer. In this paper, based on the original standard 122 finned projectile, MVG's were mounted at the projectile shoulder to investigate the effect of separation control on the aerodynamic characteristics of the projectile. Numerical simulations of the flow fields of 122 standard finned projectiles with and without micro wedges were performed with the DES method, the modifications of the boundary layer structures and aerodynamic data for two cases were compared and discussed, and the influence of micro-wedges on projectile aerodynamic forces and stability have also been investigated. Numerical results show that the micro wedges can inhibit fluid separation on the projectile surface, improve the projectile lift and pitching moment, and decrease the Magnus moment, as a result improving the flight stability and firing accuracy, which can provide guidance for the improvement of spinning projectiles.