Study and Simulation of the Thrust Vectoring in Supersonic Nozzles

The present study aims to numerically simulate the thrust vectoring by secondary injection. analysis of flow for this was done using ANSYS Fluent. kω-sst turbulence model used. baseline solver selected as a double-precision Density-based coupled solve with implicit time integration. Least squares cell-based spatial discretization in which solution assumed vary linearly used and second-order upwind scheme is interpolating values pressure, momentum, turbulent kinetic energy, specific dissipation rate, energy. computational conducted under conditions. initialization steady-state problem full multigrid (FMG) get initial boundary provided reference value. results without fluid injection are presented terms angle deflection, efficiency. These then compared those obtained or experimentally other authors. This comparison very interesting were close, error only 5%.