Lagrangian Analysis of Multiphase Flow Effects on Solid Rocket Nozzle Performance

Modern solid rocket motors are fueled by composite propellants that typically feature a high aluminum mass fraction in order to enhance the specific impulse. This gives rise to a multiphase flow, which is responsible for a significant degradation of the nozzle performances. In this work, an Eulerian–Lagrangian computational framework is employed to predict these performance losses through high-fidelity CFD simulations. The study evaluates the influence of particle size and the role of particle breakup modeling on the accuracy of the predicted flow behavior and nozzle efficiency.