Advanced computational flow analysis with experimental investigations of rocket engine nozzle

Abstract

This research offers the outcome of a numerical and experimental investigation that the influence of convergent nozzle angles on the interior features of the flow field as well as on the propulsive accomplishment of convergent nozzles A series of convergent nozzles was chosen For which Computational Fluid Dynamics CFD simulations were completed The simulations were performed using the ANSYS FLUENT version 19 0 flow solver The present research works were computed for 15 20 25 30 35 and 40 axisymmetric convergent nozzle angles with 14 16 18 20 30 40 50 60 and 70 NPRs The present numerical study is to investigate the characteristics of convergent nozzle flows by varying its geometrical parameters such as nozzle angles and NPRs The numerical analysis was conducted in SST k Omega model on a convergent nozzle at 15 deg with NPR from 14 to 70 to get the jet flow structure Centerline total pressure distribution and nozzle coefficients Varied the nozzle angles from 20 25 30 35 and 40 and repeated the numerical analysis for all mentioned NPRs newline