Computational Study on Performance of Ramjet Engine for Various Mach Numbers

This research focuses on the modelling and simulation of combustion dynamics in lean premixed 2-D axisymmetric Ramjet engine for Mach number 3, 3.5, 4 and 4.5. Current research is to establish proper premixing of flow with fuel and generate proper conditions for combustions. Intake design is the primary objective for generating proper shock waves to reduce, and it enters the ramjet during supersonic speeds. Study includes proper combustion by reducing supersonic flow to subsonic before the combustor, and also proper mixture of air and fuel. Different air fuel ratios are considered and concluded by most efficient Air fuel mixture ratio. Meanwhile, aerodynamic properties such as pressure and temperature lead us to study the flow mixture.