Modelling and Simulation of Supersonic Nozzle using ANSYS Workbench with New Measuring Data

This paper deals with modelling and simulation of supersonic nozzle using computational dynamics. We are considering the C-D (convergent-divergent) nozzle and analysis of supersonic nozzle by changing the parameters which are presently uses in the rocket have been conducted. Study also focused on discussing about the material using at the time of manufacturing of nozzle. First axisymmetric nozzle geometries were drawn on design modeller of ANSYS then analysis has done using fluent. The heat transfer rate of the outer wall and inner wall of the nozzle has been calculated and compared for various nozzle configurations. Static Pressure contours of various nozzle configurations have been plotted. Velocity and Mach number contours of various nozzle configurations have also been plotted. Graph of Mach number and heat transfer coefficient has also shown. After comparing the results it has observed by the contours that, nozzle with greater expansion gives high heat transfer coefficient compared to the conical nozzle. Parameters and laminar models considered in the study were found to give results which agreed with experiment and analytical data.