Numerical Study of Fluidic Thrust Vector Control Using Dual Throat Nozzle

Compared to a variety of mechanical vectoring nozzles, fluidic nozzles possess more research value nowadays. The dual throat nozzle is gradually developing into an outstanding technology handle supersonic and hypersonic aircraft deflections. Three-dimensional, steady, compressible, viscous flows in rectangular are numerically investigated by resolving Reynolds-averaged Navier-Stokes equations shear stress transport k-omega turbulence model. Computational fluid dynamics results verified against the existing experimental data, where good consistency gained. impacts pressure ratio, injection-to-mainstream momentum flux setup angle slot injector on systemic performance examined. Useful conclusions summarized for engineering designers. Firstly, pitching angles decline along with increasing while thrust ratio efficiency increase. Secondly, vector enlarge increase whereas both decay. Finally, remarkably. Although 120° highest, comprehensive characteristics terms 150° excellent.