摘要
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 155 mm projectile was taken as an example,and the micro-vanes were mounted at the projectile shoulder to investigate the separation control on the aerodynamic characteristics of projectile.Numerical simulations were performed with the use of DES method for the flow fields of projectiles with and without micro-vanes,and the characteristics of the boundary layer structures and aerodynamic data were compared and discussed.Numerical results show that the micro-vanes can be used to inhibit separation of fluid on projectile surface,and improve the flight stability and firing dispersion of projectile.
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 155 mm projectile was taken as an example, and the micro-vanes were mounted at the projectile shoulder to investigate the separation control on the aerodynamic characteristics of projectile. Numerical simulations were performed with the use of DES method for the flow fields of projectiles with and without micro-vanes, and the characteristics of the boundary layer structures and aerodynamic data were compared and discussed. Numerical results show that the micro-vanes can be used to inhibit separation of fluid on projectile surface, and improve the flight stability and firing dispersion of projectile.
