Simulation of Convergent Divergent Rocket Nozzle using CFD Analysis

Abstract

A rocket nozzle is a mechanical device which is designed to control the rate of flow, speed, direction and pressure of stream that exhaust through it.There are various types of rocket nozzles which are used depending upon the mission of the rocket. This paper contains analysis over a convergent divergent rocket nozzle which is performed by varying the number of divisions in mesh. Also the various contours of nozzle like Cell Equiangle skew, Cell Reynolds number, Pressure,Velocity, Mach Number,and above are calculated at each type of mesh using CFD analysis software ANSYS Fluent.