Whenever we need an appreciable manoeuvring, the ultimate choice is thrust vectoring control system, because they provide excellent survivability and improved performance in the case of gas turbines. Since, from the time of its inception many researchers worked on to reduce the number of actuators and in improving the thrust vectoring angle. Even through there are different ways to achieve greater jet deflection, mechanical type achieved the better credits. This paper focus on designing a c-d nozzle with various case of vectoring and non- vectoring to attain supersonic flow and optimizing it to achieve maximum drop pressure, velocity, Mach number with various cases. The analysis has been performed according to the c-d nozzle with various cases and keeping the same input condition. Our objective is to investigate the various case of vectoring and non- vectoring c-d nozzle. In this, initially modelling of the c-d nozzles has been done in GAMBIT and later on mesh generation and analysis has been carried out in GAMBIT FLUENT 6.3 and various contour like pressure, velocity have been taken and their variation according to different case C-D nozzle has been studied. Comparing the c-d nozzle with various degrees. Which can varying Mach number, velocity and pressure values which are used to thrust vectoring.

Keywords: C-D nozzle, GAMBIT, FLUENT