CFD modeling for flow field characterization and performance analysis of HGITVC

The present study aims at numerically investigating the performance of the Hot Gas Injection Thrust Vector Control (HGITVC) system within the divergent part of a supersonic nozzle. For this purpose, the following measures were taken: considering the flow to be compressible and turbulent, using k-ω-SST model for turbulence modeling, simulating and comparing single and dual injections using a three dimensional and multi block in-house code and validating simulation results using experimental data. The findings indicate that the strength of secondary jet rises as the injection area and injector to nozzle pressure ratio increases. Moreover, it is proved that increase in strength of injection leads to decrease in the amplification factor and increase in the deflection angle and the axial thrust. In addition, a sharp drop in the performance of HGITVC is observed not within acquired permissible range for strength of injection which reduces the system performance. These findings lead us to conclude that in comparison with single injection, the dual injection cannot increase the thrust ratio which is the main objective of this study. However, it helps to inject more gas without shock impingement phenomenon and also improves the Axial Thrust Augmentation (ATA).