Preliminary Design and Analysis of Dual Throat Fluidic Thrust Vectoring Nozzle for Supersonic Aerospace Application

The project investigates the performance characteristics of dual-throat nozzle used for fluidic thrust vectoring (FTV) in supersonic aircraft applications, offering a potential alternative to mechanical vectoring methods. Fluidic thrust vectoring provides benefits such as reduced weight, lower radar signature, and improved manoeuvrability and control. Computational methods are used to study the effects of geometric and operational parameters, including nozzle pressure ratios and secondary injection rate and injection angle, on thrust-vectoring efficiency and system dynamics. The study aims to develop optimized design configurations and validate using computational models.