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.

燃油喷射系统是超燃冲压发动机设计中非常重要的过程。本文充分研究了在马赫数为 4 的超音速气流下喷流燃料分布上上游斜坡边缘的存在。RANS 方程与 SST 湍流方案相结合，以模拟燃料射流在倾斜斜坡边缘的流动特征和扩散。本研究的主要重点是在存在超音速错流的上游斜坡的情况下分析单个氢射流的燃料混合和穿透。研究了斜面不同角度下混合区的大小。我们的结果表明，上游斜坡的应用极大地影响了进入的超音速气流，并改变了靠近射流的涡流强度。我们的结果表明，斜角的混合性能比斜角高 45%。将斜率和斜坡角从 10 度增加到 30 度，可使燃料喷射下游的燃料混合增加 55%。