The numerical simulation is carried out to study the flow characteristics and aerodynamic performance of the dual throat thrust vectoring nozzle. The effects of both the primary nozzle pressure ratio (NPR) and the secondary jet flow rate on the aerodynamic performance and internal flow characteristics are analyzed with and without thrust vectoring. The results indicate that the dual throat nozzle has the optimal thrust ratio and discharge coefficient of 0.974 and 0.935 at NPR=3.0—4.0 on un-vectoring thrust state. The dual throat nozzle has the optimal thrust vector angle and thrust ratio at NPR=4.0 on vectoring thrust state, and the largest thrust vector angle of it is as high as 16.1°. The thrust vector angle and the thrust ratio reach to the peak value of 14.6°and 0.95 at the point of secondary jet flow rate is 4%. The thrust vector angle is increased with the enhancement of the secondary jet flow rate and decreases gradually when reaches to a critical value. Both of the thrust vector angle and the thrust vector efficiency are reduced with the increment of primary nozzle pressure ratio under the constant secondary jet flow rate. The thrust ratio is increased as the increasing of primary nozzle pressure ratio and decreased after reaching to the maximum at NPR=4.0. While the discharge coefficient is increased as the increasing of primary nozzle pressure ratio and tends to stable after reaching to the maximum at NPR=4.0. .