Monte Carlo Simulation of a Rarefied Multiphase Plume Flow

摘要

Exhaust flows from solid propellant rockets are characterized by a number of complex and often overlooked phenomena which should be considered for accurate numerical modeling. In a typical solid rocket motor (SRM), a 10 to 20% mass fraction of aluminum powder is used to reduce combustion instabilities and increase specific impulse. Within the combustion chamber, this aluminum content undergoes a complicated process of melting, heretogenous combustion, evaporation, agglomeration, and breakup.