Investigation of mixing and Combustion in supersonic flows

The significance of green transportation at hypersonic speeds is the current field of research for space launchers and commercial trans atmospheric vehicles. However, due to their high speeds at Mach > 1, results in a very short residence time of the order of few milliseconds (10-3 – 10-4 s) minimizing the chances for air-fuel barely mix and burn. Furthermore, the interaction of fuel injection at sonic speed via transverse and cross flow with incoming airstream at high Mach results in the generation of complex vortices that effect the chemical kinematics and combustion and are influenced by the dilatational term “∇.U”. therefore, the supersonic combustion region is affected by compressibility and the corresponding baroclinic terms. Thus, it is very important to realize the behavior of flow while different injection angles, the geometry of the cavity and the corresponding flow behavior. This could be realized by the numerical simulation of flow to better understand the physics of supersonic combustion. Therefore, the current study plans to understand the shock and how it interacts with fuel injection and mixing, the resulting vorticity development, the effects of adding heat and boundary layer separation on total pressure loss by utilizing large eddy simulations.