Design and Computational Flow Analysis of Different Rocket Nozzle Profile

Abstract

In recent days the launching value of increasing the industrial business starts with lowering prices related to the launch vehicle operation. Reducing the price begins with rising the propulsion systems, creating these vehicles a lot of economical with a restricted fuel amount. The Linear Aerospike engine has incontestable bigger thrust potency over this engines used on launch vehicles. However, unresolved problems with warming plague this standard. This study proposes an approach amendment to the rocket motor that explores a way to increase the performance of the nozzle body, and lower the chance of failure because of the acute pressure environments. The results show that however the most exhaust flow of an Aerospike is full of couture of the spike surface. Victimization in Ansys CFD software system and acting a straight forward experiment with whoosh rockets, the study explores however exhaust flow changes the performance characteristics, in the main speed close to the wall. The results with some improvement is created by CFD nozzle flow studies, to make sure the bottom pure mathematics isn't a contributory issue to the film-cooling results.