Abstract

Delft Aerospace Rocket Engineering has developed a 1 kN hybrid rocket motor, using Nitrous Oxide\nas oxidizer and a mixture of Sorbitol and Paraffin as fuel. The thesis starts with the numerical simulation of the rocket motor firing. The simulation provides the trend over time of motor parameters such as mass flow rates, vapor quality of the oxidizer. Once validated through comparison with the test data, these values have been used to setup CFD simulations of the combustion chamber.