Thrust Enhancement of a Convergent-Divergent Nozzle by Using CFD

Abstract

The CFD analysis of a convergent-divergent nozzle has been conducted at various divergent angles. Different geometries of nozzles have been created by changing the divergent angle. For modeling and meshing of nozzle, ICEM CFD was used and for analysis CFX-12.0 was used. The inlet boundary conditions were specified according to the available information. Here k-epsilon turbulence model is used. Governing equations were solved using the finite volume method in ANSYS CFX software. Results are obtained by CFD-POST. Exit velocity and Mach number was increased with increase in divergent angle. Based on the maximum exit velocity obtained, that nozzle geometry is optimized. For still more increase in the exit velocity, radius at the throat has been done on the optimized model and analysis was been carried out. Exit velocity was increased to certain extent and this was taken as final optimized model. Therefore, the final optimized nozzle will reduce the fuel consumption and shock's formation, increases the thrust and exit velocity to a maximum level.