Parametric Study on Thrust Vectoring with a Secondary Injection in a Convergent–Divergent Nozzle

Abstract

This work investigated the performance of thrust vectoring with a secondary injection in a convergent–divergent nozzle. Analytical modeling was conducted to determine the shock location and shock angle, providing a guideline for system design and performance. Thereafter, numerical simulation was performed to understand the effects of the injection pressure, injection location, injection angle, and injectant on thrust vectoring performance. Satisfactory agreement between the analytical modeling and numerical simulation suggests that shock reflection within the nozzle must be avoided to produce efficient thrust vectoring. Numerical results showed that both the injection pressure and the injection location have significant impacts on the thrust angle. The lateral thrust, and hence the thrust angle, was found to increase with the injection pressure and to be larger when the injection was situated closer to the nozzle exit. Impacts of the injection angle and the injectant on the thrust angle were found to be insignificant. However, hydrogen peroxide (H2O2) can be more effective at producing a side thrust than can air.