Abstract
The fuel injection system is a highly significant process in the design of the scramjet engine. In this paper, the presence of the upstream ramp edge on fuel distribution of jet flow at supersonic air stream of Mach = 4 is fully investigated. RANS equations are coupled with SST turbulence scheme to model the flow feature and diffusion of the fuel jet flow in attendance of angled ramp edge. The main emphasis of this study is to analyze fuel mixing and penetration of a single hydrogen jet in the presence of an upstream ramp at supersonic cross-flow. The size of the mixing zone at different angles of the ramp is investigated. Our results show that the application of the upstream ramp substantially influences the incoming supersonic airflow and changes the strength of vortices close to the jet. Our results show that the mixing performance of the ramp angle is 45% more than the slope angle. Increasing the slope and ramp angle from 10 deg to 30 deg increases the fuel mixing up to 55% downstream of the fuel jet.