Design and analysis of a rocket C-D nozzle

Abstract

The design is based on previous designs used as a benchmark for ours. Since the rocket propulsion for various purposes such as manned missions or launching satellites into orbit are increasing, a nozzle is an integral part that deserves attention. Keeping that clearly in mind, a basic design is done using the knowledge of compressible flow. The values of temperature, pressure and velocity is needed at every section of the nozzle so as to design the shape, insulation and cooling arrangements for the nozzles and the thrust for the same is calculated. Using the design, theoretical calculations are done and CFD simulations are also done. The test result for the both methods is obtained by simulation and theoretical calculation of the flow. In addition, the calculations and the results obtained from using ANSYS Fluent software and Theoretical calculations are compared under the basis of their values. The validation of these formulae is carried out using the Computational Fluid Dynamics (CFD) software ANSYS Fluent.