Computational Investigation of Injection Effects on Shock Vector Control Performance

This paper presents a computational investigation of Fluidic Thrust Vectoring (FTV) to evaluate the use of fluidic injection to manipulate flow separation and cause thrust vectoring of the primary jet thrust. In particular, the simulation of a two-dimensional convergent- divergent nozzle with Shock Vector Control (SVC) is performed using UNRANS equations with Spalart-Allmaras turbulence model. Computational results indicate that the nozzle thrust performances are strongly dependent by the nozzle pressure ratios and by the secondary mass flows. For this reason a parametric study has also been performed with the aim to initiate a database of the nozzle performances with different parameters affecting the thrust vectoring and the pitch thrust angles. Comparisons with experimental results are used to validate the numerical procedure.