In this work a density-based numerical modeling for internal ballistic parameters of solid rocket motors is developed. The replacement of propellant surface is modeled by dynamic mesh method. The effect of addition of three different types of nano-metal additives is investigated while the erosion phenomenon is considered. These parameters are tested for a nozzle less and a rocket with convergent- divergent nozzle. The achieved results show that regression rate of propellant surface for a rocket with nozzle is more significant, also amongst the different turbulent models the k-w SST model is more compatible with the physical condition.

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