Flow Analysis Of Supersonic Nozzle For Rocket Propulsion System

A supersonic nozzle normally has a converging-diverging shape, in which high-pressure gases pass through the throat and expand in the diverging section to attain supersonic velocity and generate thrust. When the exit area of the nozzle is changed, the expansion of gases at the outlet also changes, which directly affects pressure, velocity, Mach number, temperature, and thrust performance. In this project, the basic nozzle profile is maintained and only the exit area is varied by creating three different nozzle models to study the influence of exit area on the flow characteristics of a rocket propulsion system. The main purpose of changing the exit area is to identify which nozzle configuration provides better gas expansion and improved propulsion performance. A proper exit area can increase exhaust velocity, reduce pressure losses, improve thrust efficiency, and provide stable supersonic flow at the nozzle outlet. All three models are designed in Creo using Ni-Co-Cr- alloy-wrought alloy as the selected material, and the flow analysis is carried out in ANSYS Fluent through CFD simulation. By comparing the results of the three models, the most suitable exit area can be identified based on better pressure distribution, velocity, Mach number, and thrust behavior. Thus, this project provides a simple and effective method for optimizing supersonic nozzle design and improving the efficiency of rocket propulsion systems.