Experiment on fluidic thrust-vectoring nozzle based on shock control concept

An experimental investigation for the aerodynamic effects of fluidic injection in a two-dimensional,convergent-divergent(2DCD) nozzle has been conducted.Simulations were performed at static conditions of a single fluidic injection port with variable injection angles(60°,90° and 120°)at a relative position of x/xl=0.688,with the scheduled nozzle pressure ratios(NPR,from 4.5 to 13.89) and secondary to primary total pressure ratios(SPR) from 0.4 to 1.0.Results indicated a pressure rise on the nozzle wall centerline.It validated that the nozzle thrust vectoring angle and thrust coefficient change with different NPRs,SPRs and injection angles.