CFD Analysis of Nozzle Flow with Sudden Expansion In Aerospace Engineering

Abstract

As the need for missiles and rockets has increased exponentially, the challenges associated with the gas dynamics of these vehicles continues to be a concern. The pressure in the downstream is sub atmospheric whenever there is a sudden expansion. This low pressure in the recirculation zone causes significant drag, accounting for almost two-thirds of the net drag of the aerospace vehicles. Hence, the purpose of this paper is to deliver a Computational Fluid Dynamic (CFD) analysis of the impact geometry and flow parameters have on the thrust force generated by the flow from convergent divergent nozzles to a suddenly expanded circular duct with a wider cross-sectional area. By observing all of the results, it is possible to conclude that the flow field in an enlarged duct is greatly influenced by the area ratio.