Numerical simulation of fluidic thrust vectoring in an axisymmetric supersonic nozzle

Transverse secondary gas injection into an axisymmetric supersonic nozzle under standard atmosphere pressure is investigated to get the performance of thrust vectoring control. An analytical model was established based on the transverse injection flow. Three-dimensional CFD methods were performed with different transverse secondary injection models. To validate the ability of the numerical model, numerical results were compared with the analytical and experimental results. Overall pressure distributions show quite good match with the analytical and experimental results. The Mach number contours in different injection positions were obtained. Reflection of the bow shock occurred for x j / L = 0.6 , not for x j / L = 0.9 . Nozzle pressure ratio is also the key factor for shock vector control. Based on this data, thrust vectoring efficiency and system thrust ratio have been considered. Finally, the pressure distributions in different momentum flux ratios were studied in CFD and analytical models. The separating point of boundary layer is moving upstream with the increasing of momentum flux ratio. The result will provide the reference to the further development of shock vector control.