Three-dimensional Reynolds average Navier-Stokes equation was solved by using the time marching method in finite volume

and circular convergent-divergent nozzle flow fields in shock induction control vector scheme were numerically simulated.Injection pressure ratio and nozzle pressure ratio were considered in numerical analysis in this paper.The results indicate that

thrust vectoring can be obtained through the shock induction control scheme to turn the main flow.The vector angle reaches 15.35° when the nozzle pressure ratio is 4 and injection pressure ratio is 1.499.Through analysis

the shock surface formed in the circular exhaust nozzle was three-dimensional

and its configuration was complicated.The computational analysis is helpful for better understanding of the flow field structure of vectoring nozzle in experiments.