3D computational study of thrust vectoring using bypass mass injection in a propulsion nozzle

For modern supersonic vehicles, thrust vector control is a conspicuous prerequisite to accomplish high performance aerospace applications. Thrust vector control chiefly falls into a few classifications, for example, mechanical thrust vector control and shock vector control. Shock vector control is outstanding amongst other approaches to achieve this thrust vector control. A bypass mass injection is used to generate shock vectoring in a planar supersonic Convergent-Divergent (CD) propulsion nozzle in this study and a 10×10 square mm bypass channel was used for the injection. This bypass mass injection is kept perpendicular at the diverging section of the studied nozzle. Overexpanded nozzle flow is achieved by carrying out the investigation at Nozzle Pressure Ratio (NPR) of 3.0. The flow conditions and size of the square injection channel ensures the bypass mass flow ratio around 5%. Reynolds-Averaged-Navier-Stokes (RANS) equations with k-ω SST turbulence model have been applied through numerical computations to capture the three-dimensional steady characteristics of the flow field. Results show that the shock structure becomes asymmetric due to the bypass mass injection along with the formation of recirculation zone near the bypass mass injection. Moreover, a considerable thrust vectoring can be achieved due to the asymmetric velocity distribution at the exit plane.For modern supersonic vehicles, thrust vector control is a conspicuous prerequisite to accomplish high performance aerospace applications. Thrust vector control chiefly falls into a few classifications, for example, mechanical thrust vector control and shock vector control. Shock vector control is outstanding amongst other approaches to achieve this thrust vector control. A bypass mass injection is used to generate shock vectoring in a planar supersonic Convergent-Divergent (CD) propulsion nozzle in this study and a 10×10 square mm bypass channel was used for the injection. This bypass mass injection is kept perpendicular at the diverging section of the studied nozzle. Overexpanded nozzle flow is achieved by carrying out the investigation at Nozzle Pressure Ratio (NPR) of 3.0. The flow conditions and size of the square injection channel ensures the bypass mass flow ratio around 5%. Reynolds-Averaged-Navier-Stokes (RANS) equations with k-ω SST turbulence model have been applied through numerical computatio...