To understand internal flow transformation using secondary fluidic injection for throat aero control, Numerical simulation studies of the solid rocket motor were conducted under two-dimentional two-phase nozzle flow. This concept of fluidic throat control featured symmeteric injection around the nozzle throat to provide throttling to vary effective throat area and skew the sonic plane, namely the nozzle thrust vector can be controlled. The investigation sought to maximize the effetive range of primary nozzle throat area control, while minimizing any detrimental effects on gross thrust due to the secondary injections. Under the assumption of constant velocity drag coefficient for two-phase flow, the computational fluid dynamics program with the structured-grid have been completed to investigate effects of injector geometry, angle, massflow ratio, and flow properties on performance in our research group. This paper presents the interaction between primary stream and secondary flow, and analyzes the sonic plane skewing in detail. A fixed-geometry nozzle was designed, and the nozzle parameters and injector configurations were introduced. The Mach number distributions of flow field, the particle tracks, and the flow line at different conditions were given. The effects and rules of different injection parameters on the efficient area of two-phase aerodynamic throat were studied. The flow characters of two-phase aerodynamic throat were gained, and two main approachs to strengthen the ability of throat area control, which were increasing injector massflow ratio and secondary flow resistance, were summarized from the simulation results. In the next stage, the optimum design method of fluidic injector parameters will be invetigated further.
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