DESIGN AND ANALYSIS TURBULENCE MODEL FOR TESTING THE SOLID ROCKET MOTOR

Abstract

Design of a Solid Rocket Nozzle as well as the Computational Study of Flow Analysis through Nozzle will be carried in the Present 
Project by accelerating exhaust gases at very high-speed rocket engines generates Thrust. Nozzle Design is a multi-objective 
approach as it depends on various factors and plays an important role in the whole performance of the Rocket. After reaching certain 
altitude, it is very difficult to Control and Stabilize the Rocket using control surfaces due to the absence of atmosphere. So, our aim is 
to Design the Nozzle which can be applicable for the Reaction Control System (RCS), which is the mechanism used in rockets for 
controlling in the absence of Atmosphere. For this purpose, initially the Design Procedure, Design Aspects and the Performance of 
Nozzle with respect to Altitude will be studied and then Ideal Rocket Nozzle will be designed which can operate successfully at high 
altitudes.