Investigation of the effect of geometrical parameters on channel flow in non-reacting supersonic flow conditions with presence of cavity

In the present work, the flow inside a channel with cavity is investigated as a Scramjet combustion chamber. For this aim , the parameters such as L/D (cavity length to cavity depth), H/D (channel height to cavity depth) and varied Mach numbers are studied in the supersonic flow to investigate the effect of geometric parameters on channel flow in non- reacting conditions. In this work, the vorticity is used as mixing parameter. Two-dimensional Navier-Stokes equations are used to solve the steady-state flow. The density based method and standard k-ε Model are employed to numerical simulation. The results show that vorticity of boundary layer and thus mixing in flow is increased with growing of L/D, Mach number and having sweep angle for cavity. Geometries with larger H/D performed better than other geometries in terms of generating vorticity and reducing Total pressure loss. Although the H/D = 1 ratio has a higher recirculation than others, it will not be reliable for all supersonic flow because of its considerable total pressure loss and the survival of the oblique shock in some conditions.