Abstract: To analyze how the bipropellant thruster injection angles influence the liquidfilm distribution, we propose a numerical method to calculate the distribution of the liguidfilm on the inwall of combustion chamber with different injection angles by using the finite volume method. The proposed approach is based on the gasliquid biphase model under the assumptions there is no combustion in the combustion in the combustion chamber, and the propellant is all NTO. The calculation results show that the liquidfilm moves to the direction of injector as injection angle increase. The lengths of liquidfilm are all around 30mm under different injection angle. However, the liquidfilm thickness changes a lot when half injection angle is between 45°and 55°.

Key words: bipropellant, liquid film distribution, injection angle