The aerodynamic effects on fluidic thrust vectoring of a two-dimensional

convergent-divergent(2DCD) nozzle with fluidic injection were simulated numerically

showing that different fluidic injection positions have bigger influence on the vector angle.In the case of nozzle NPR=4.5

the vector angle of secondary injection position is maximum in relation to the divergent middle section of nozzle

in the case of nozzle NPR≥7.2

the vector angle becomes bigger if the secondary injection position is closer to the outlet.The results indicate that vector angle is sensitive

and thrust coefficient and discharge coefficient are insensitive to the injection position.