Analysis on Solid Rocket Motor Using Computational Method for Uniform Flow Field

The purpose of this paper is to get a complete study of flow parameters over a typical solid rocket motor and further analyze it according to the desired particular needs. Solid rocket motor consists of key inert components, namely the motor case, igniter case, and nozzle. The motor attached to the thrust vector control mechanism in a large-scale rocket can also be considered to be an important component. The paper follows the trait of a numerical study of the uniform flow equations, motor design, and computational fluid dynamics analysis over the motor using ANSYS. The analysis is done on the solid rocket motor for various parameters like dynamic and static pressure over the surface, surface shear stress and mainly focusing on the flow velocity. The detailed study of flow velocity includes the streamlined flow attached to the surface and the possible vortex formation areas over the motor case surface. Here, the calculations are done at a flow field velocity of mach 0.6.