Abstract: The flow fields of the two-dimensional fluidic throat skewing vector nozzle were simulated numerically. The effects of the single side injection at the throat and the assisted injection at the divergent section on the flow and the performance of the nozzle were studied. These simulations show that the single side injection at the throat can generate an asymmetric flow, and result in thrust vector, but the vector angle is smaller; the assisted injection at the divergent section can improve the nozzle thrust performance remarkably; only with the larger injection flux, there will be a typical "throat skewing" phenomenon; however, the highest efficiency region of thrust vector control is not occurred after the "throat skewing" phenomenon, but in the process of the forward movement of the bow shock position and the expansion of the subsonic region upstream of the divergent section injection inlet.