Numerical and Experimental Analysis of a Paraffin-based 1000 N Thrust Class Hybrid Rocket including Nozzle Erosion

Reynolds–averaged Navier–Stokes (RANS) simulations with sub-models of turbulence, chemistry, fluid-surface interaction, and radiation of the internal ballistics of a 1000 N paraffin- oxygen test motor are performed in this work. The objective is to rebuild the experimentally obtained fuel regression rate and graphite nozzle erosion through multiphysics numerical simulations. Firstly, the effects of the pre-chamber and post-chamber cavities at the initial, average, and final diameter of a reference burn are assessed to be negligible for the internal flowfield reconstruction, but useful to increase accuracy of pressure and combustion efficiency estimation. Then, a sensitivity analysis of the finite-rate global chemical reaction mechanism in terms of its reaction rates is performed. Finally, numerical simulations modeling the fuel shape change in space and time show a more accurate comparison with experimental data. Finally, graphite nozzle erosion rate experimental data are successfully rebuilt numerically.