Numerical Investigation on Influence of Precursor Flow on Combustion in Muzzle Flows

Abstract

The muzzle flow with and without precursor flow is simulated. The AUSM+ (Advection Upstream Splitting Method) scheme is adopted to capture the shock waves in the muzzle flow. The combustion in the muzzle flow is considered using detailed reaction kinetics model. The model consists of 9 species and 12 reactions. Besides, an inert species is added to trace the precursor gas. By analyzing the motion of the inert gas, the interaction of the precursor gas and the propellant gas is obtained. By comparing the results of the muzzle flow, the influence of the precursor flow on the muzzle flow is discussed in detail. The present of the precursor flow makes the jet boundary more complex and increases the intensity of combustion.