Performance and Emission Analysis of a Diesel Engine Retrofitted with a Gunmetal-Based Porous Medium in the Cylinder Head
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Abstract
This paper presents a comprehensive investigation of non-linear compressible flow dynamics in supersonic propulsion systems using computational fluid dynamics (CFD) simulations. The study focuses on modelling and analysing the behaviour of supersonic flow within a converging-diverging nozzle, emphasizing key flow parameters such as pressure, temperature, and Mach number distributions. Utilizing the compressible Navier-Stokes equations and the k-ω SST turbulence model, the simulation accurately captures the interactions of shock waves, expansion fans, and boundary layers. Results show a significant pressure drop from 500,000 Pa to 160,801 Pa, and a temperature decrease from 300 K to 204 K as the flow expands and accelerates to Mach 2.0. These findings validate the nozzle’s design, demonstrating efficient energy conversion from thermal to kinetic energy, with minimal flow separation and shock-induced losses. The smooth profiles of key parameters indicate the absence of strong shock waves and boundary layer separation, critical for optimal nozzle performance. This research provides valuable insights into supersonic propulsion systems' flow dynamics, offering a foundation for optimizing nozzle geometries and enhancing propulsion efficiency. Future work will explore more complex flow conditions, including multi-phase flows and chemical reactions in high-temperature environments.
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