Numerical Study on Secondary Jet Injection of Fluid for Thrust Vectoring in 2-D Supersonic Nozzle

Maneuvering of high speed aircraft is a challenging part during designing of the jet aircrafts in which various proposals had come with many solutions which includes the Secondary fluidic thrust vectoring. Here the study is performed to observe the flow variation by injecting the secondary fluid at eh exit of the nozzle. In supersonic nozzles due to injection of secondary liquid we observed shock and formation of these shocks are studied well. Fluidic thrust vectoring with the shock vector control method is widely studied at the moment, requires forced, asymmetric fluidic injection of a secondary air stream into the supersonic, primary flow that develops in the divergent section of the nozzle at certain conditions. This technology also can improve aircraft maneuverability by manipulating the nozzle flow to deflect from its axial direction our main objective is to investigate the effect of a secondary jet on the primary flow in a converging-diverging nozzle, and to find the location of the FTV nozzle and angle of injection for the secondary fluid.