Abstract: The new type of two dimensional thrust vectoring nozzle with the secondary flow injection was studied by using experimental method and CFD method.The experiments were finished in a supersonic wind tunnel in NPU.The wall pressure and the thrust vector angle were measured for the different secondary flow pressure under the constant main flow pressure.The flow field and performance of the nozzle were also analyzed by the computation of Reynolds averaging N S equations with the time marching finite volume method.The computed results were compared to experimental data in a good agreement.Both the experimental and computational results showed that the pressure of secondary injection flow should be large enough to create a vectoring thrust.In our case the threshold ratio of the total pressure of the second flow to that of main flow was 0 32 and the maximum deflection of the thrust vector was 46°.