Study and Simulation of the Thrust Vectoring in Supersonic Nozzles

Abstract

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