Advanced Computational Flow Analysis - Rocket Engine Nozzle Kumar S. Senthil*, Arularasu M.** *Assistant Professor, Nehru Institute of Engineering and Technology, Coimbatore, Tamil Nadu, India **Principal & Professor, Thanthai Periyar Government Institute of Technology, Vellore, Tamil Nadu, India Online published on 9 November, 2016. Abstract Analysed a rocket engine nozzle to understand the phenomena of various design conditions under the different convergent angle, divergent angle and throat radius by Computational Fluid Dynamics (CFD). Convergence problems regarding rocket nozzle is analysed in different angles. In our research work various inlet boundary conditions are considered with experimental information. The research paper focused on static pressure optimization and Mach number optimization. The experimental values on the basis of results along by optimal values of nozzle design parameters obtained from optimization techniques applied are in COMSOL software system. Angles converged and Diverged and Throat radius are considered. The reaction flow of static pressure and Mach number values of computational fluid dynamic is analysed. Top Keywords Rocket engine, Nozzle, CFD, Mach Number, Divergent angle, Convergent angle, Static pressure. Top |