CFD Analysis of Different Shape Rocket Nozzles
摘要
The nozzle is a device used at the end of the rocket so as to provide thrust to the rocket to propel. It provides thrust to give momentum and propel any aerospace vehicle. The nozzle design configuration plays a very crucial role in aerospace vehicles. And, it is configured according to the various applications. In the present work, we have attempted CFD investigation on two different shapes so as to compare the performance by estimating the thrust. The two different nozzles which were studied in the present work are (a) the convergent–divergent nozzle and (b) the bell-shaped nozzle. The CFD analysis is carried out using ANSYS 22.0 software to obtain velocity, pressure, temperature, and the flow pattern.