Abstract: Two-dimensional internal flow field of thrust-vectoring nozzles was calculated at two fluidic thrust-vectoring concepts of shock vector control and fluidic throat skewing. Base on the partition method of quadrangular structured meshes which were densified partly, the Navier-Stokes equation was solved by means of second order upwind disperse schemes and two-equation turbulent model, and the thrust-vectoring performance of fluidic thrust-vectoring nozzle was got through numerical simulation of internal flow field. The results indicate that for shock vector control, small nozzle pressure ratio and large inject mass flow rate would result in larger vector angle; for fluidic throat skewing, smaller flap injector angles would result in larger vector angle without thrust loss; fluidic throat skewing concept is prospective for its smaller thrust loss, lower nozzle weight and cost.