Steady numerical study of aerodynamic throat formed by round injectors

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.