Abstract: In order to investigate the effects of geometrical parameters on the mixing performance of the injector of fuel/air mixture for the forebody/inlet of shock-induced combustion ramjet (shcramjet) at high Mach number，finite volume implicit RANS numerical simulations were conducted to study different cantilevered ramp injectors for comparison. The obtained results show that，the mixing efficiency of the case of 15° compression angle increases by 9%，which has larger fuel penetration，while total pressure recovery decreases by 30% compared with the benchmark. In particular，the total pressure loss is two times higher for the case of 15° compression angle than for the benchmark. Additionally，mixing efficiency of the case of 0° expansion angle is 11% superior to that of the benchmark throughout the flowfield，with larger total pressure loss. The mixing efficiency and fuel penetration of the sweep model approximately remain the same compared with the benchmark. And the negative sweep angle can reduce the total pressure loss. Moreover，the total pressure loss and mixing efficiency in the near region of the different array spacing injectors are similar. In the end of the mixing process，the injector of array spacing 20mm reaches a better mixing level. The fuel and air mix fiercely in the distance of 50～150mm.

Key words: Shock-induced combustion ramjet；Cantilevered ramp injector；Mixing performance

摘要： 为探索高马赫数下激波诱燃冲压发动机前体/进气道喷注器构型参数对燃料/空气混合的特性的影响，运用隐式RANS仿真，对不同构型的悬臂斜坡喷注器进行了三维数值模拟并进行了对比研究。结果表明，15°压缩角构型最终的混合效率比基准构型高9%且有较大的燃料穿透度，同时会付出30%的总压损失代价；15°压缩角构型的总压损失是10°压缩角构型的两倍；0°膨胀角构型的混合效率始终高出基准构型11%，但有较大的总压损失；后掠构型与基准构型相比混合效率，燃料穿透度基本不变，负的后掠角总压损失最小；三种不同喷注间距的喷注器总压损失大小基本相同，近流场的混合效率相差不大，混合终了阶段，20mm喷注间距喷注器的混合效率达到了较高水平；50～150mm是燃料/空气掺混剧烈发生的区域。

关键词: 激波诱燃冲压发动机；悬臂斜坡喷注器；混合性能