Shock vectoring control (SVC) is an important method of fluidic thrust vectoring (FTV) for aero-engine exhaust system. It behaves better on nozzle of high pressure ratio, and is considered as an alternative TV technology for a future aero-engine with high thrust-to-weight ratio. In this paper, the Flow mechanism and vector performance, including the vector angle (δ p) and thrust coefficient (Cfg), of 2D and axisymmetric SVC nozzles were investigated after the validation of turbulence models by experimental data. The influence of aerodynamic parameters, e. g. nozzle pressure ratio (NPR), secondary pressure ratio (SPR) and free-stream Ma number (M∞ ) on Flow characteristics and vector performance were studied numerically, and results show that unbalanced pressure distributions on nozzle internal walls determine δ p, while shock waves dominate thrust loss, referring to Cfg. The “ pressure release mechanism” of an axisymmetric SVC nozzle causes vector angle about 16. 54% smaller than that of a 2D SVC nozzle at NPR of 6. The induced shock wave interacts with nozzle upper wall at SPR of 1. 5, and results in the δ p of a 2D SVC nozzle 12% smaller. A new parameter (Fy, modi) of side-force was redefined for free-stream conditions, taking the pressure distributions on nozzle external walls into account. Results indicate that pressure connection on nozzle external walls of an axisymmetric SVC nozzle causes vector performance better at M∞ >0. 3 and the δ p is about 11. 2% larger at transonic conditions of M∞ of 0. 9 and 1. 1.