Numerical simulation of combustion chamber and nozzle flow in classical hybrid rocket motors

In a typical hybrid, the fuel is a solid and the oxidizer is a liquid. A combustion and flow characteristic is the key problem in a hybrid rocket motor. Making research on computation of a combustion chamber and nozzle flow of a hybrid rocket motor is necessary. Numerical solutions of full Navier-Stokes equations with chemical reaction flow were obtained for of the LOX/HT-PB hybrid rocket motor. Lower-Upper decomposition scheme and MUSCL-type and VanLeer approach were used. One step chemistry model and two steps chemistry model were adopted. The combustion chamber and the nozzle flow under oxidizer velocity and combustion pressure were calculated. The better chemistry model was chosen by the result, which will be useful for the hybrid rocket motor design.