Optimization of Convergent –Divergent Taper Angle with Combustion Chamber of Rocket Engine through Numerical Analysis

Abstract

Present days speed of vehicle is concerned in both sub -sonic vehicle( like car, bus and truck etc) super -sonic vehicles (like rockets). Convergent divergent component is the main part which decide the speed of any vehicle. A attempt is made to find the optimal convergent angle (inlet taper angle ) and divergent angle(outlet taper angle [ .) with the help of Numerical analysis through ANSYS 19.0(R3). Deciding parameter for greater thrust is angles i.e.; and [ . So, Convergent divergent nozzles with combustion chamber is designed, modelled and analysed numerical for getting optimal values of convergent and divergent angles . The various angles used are [35,15] [35,20] [35,25] [40,15] [40,20] [40,25] [45,15] [45,20] [45,25]. At these different angle the parameters such as velocity, temperature, pressure and Mach numbers are estimated with the help of steady state fluent with carbon dioxide as inlet to the combustion chamber.