Studies have shown that micro-wedge vortex generators (MVG) can effectively control the flow separation of supersonic boundary layer. In order to improve the flight stability of spinning projectile, the original standard 155mm projectile was taken as the example, and micro vanes were mounted at the projectile shoulder to investigate the separation control on the aerodynamic characteristics of the projectile. Numerical simulations were performed with the use of DES method for the flow fields of the projectile with and without micro vanes, the characteristics of the boundary layer structures and aerodynamic data for above two cases have been compared and discussed. Numerical results show that the micro vanes can inhibit fluid separation on the projectile surface, improve its flight stability and firing dispersion. Our results can provide important guidance for the improvement of supersonic projectiles.
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