A three-dimensional (3-D) numerical simulation of aerodynamic throat formed by secondary flow from round injectors

which was applied to solid propellant rocket motors

was performed in this paper.The typical 3-D flow structure and mass flow character of round injectors were reviewed.The influence of different injector area ratios

injector numbers

injection angles

injector types and major nozzle parameter were studied.The results show that the mass control performance of aerodynamic throat can be obviously improved by increasing injector numbers

applying reverse injection or convergence injector type at the same injector area ratio.