Shock vector controlling (SVC) nozzle, based on confined transverse injection and shock wave/boundary layer interaction, offers an alternative for future aircraft thrust vectoring (TV) exhausting system, due to its simple structure, low weight, and quick vector response. In the paper, the flow mechanism of SVC nozzle was studied by numerical simulation after the validation of computational fluid dynamics (CFD) models was confirmed. Then, the influence of substantial affecting factors, including injection configurations and injection angles, on the confined transverse injection flowfield characteristics and vector performance was investigated numerically. The results show that the “λ” shock wave induced by the jet injection causes unbalanced side force for the primary flow deflecting, and under larger secondary pressure ratio (SPR), the induced shock wave interacts with upper wall, weakening the thrust vector efficiency; with the increase of injection orifice numbers, the vector angle of SVC nozzle rises and is less than that of slot injection configuration; under smaller SPR, the thrust vector angle increases with the injection angle. For the case of SPR = 1.0 and 1.2, there exist optimal injection angles at which the maximum TV angle achieved.