Numerical Simulations of a Paraffin-Hydrogen Peroxide Hybrid Rocket with Swirl Injection

In this work numerical simulations of a hybrid rocket engine burning hydrogen peroxide and paraffin wax are performed with an axisymmetric RANS model, taking into account the effects of fluid-surface interaction, turbulence, chemistry, radiation and swirl injection. Simulations are performed at different swirl intensities and with two different fuel formulations to assess the effect of the swirl number and of polymeric additives on the internal ballistics. Parametric laws for the the space-averaged regression rate and combustion efficiency as a function of the swirl number are provided. Finally, an analysis on the effect of the post-chamber on the propellants mixing is performed.