Design and analysis of rocket nozzle to determine optimum material and fuel.

Nozzle is considered as one of the most important parts of the rocket propulsion system. The thrust Produced by the Nozzle will determine the performance of the nozzle i.e., the amount of load that can be lifted by the nozzle against the gravity. Heavy rockets have nozzles that can lift higher loads. The thrust produced by the nozzle will depend on parameters such as velocity at exit of the nozzle, pressure at the exit of the nozzle and etc. The thrust produced by the nozzle will also depend on the type of the nozzle indirectly as various nozzles will have various properties. The exhaust gases produced after combustion when they pass through the nozzle the pressure energy of the flue gases will convert into the kinetic energy resulting the thrust required for the lift off. In this paper we designed the nozzles using Rocket propulsion analysis software and modelled using Solid works and analysed using ANSYS to determine the optimum nozzle design and the material is optimised by using the structural Analysis of the nozzles designed. The geometry parameters such as area expansion ratio, throat diameter and type of nozzle will influence the performance of the nozzle. The effect of the area expansion ratio on the performance will be discussed. [ABSTRACT FROM AUTHOR]