Numerical analysis of flow field characteristics of supersonic submunition with parachute

The flow field of the supersonic submunition with parachute has a big influence on its aerodynamic performance. The analysis of its characteristics and law of variation can provide reference basis for its design and usage. CFD simulations of flat-faced submunition with disk-streamer parachute were carried out based on multi-block structured grids. Finite volume method and SST turbulence model were used in the simulation. The flow fields were displayed by numerical schlieren method. The results show that the flow field of the submunition with parachute is complicated and has several shock-wave and flow patterns. It is concluded that the flow field of the parachute influences counterpart of submunition and decreases its wake stagnation distance. The type of flow field can be divided into open type and closed type by the neck station of the submunition wake, and has a big influence on the drag coefficient of the parachute. As the Mach number increases, both the detached distance of the submunition's head shock and wake stagnation distances of the parachute and submunition decrease, as well as the decline amplitudes.