中文摘要：

高超声速进气道在宽马赫数工作范围内保持高性能一直是个技术难点。设计了一种曲面乘波压缩进气道，并通过改变封口激波马赫数以满足宽马赫数范围内（Ma4．5～Ma6）高性能的要求。数值及实验研究结果表明：适当降低进气道的封口马赫数（从 Ma6降至 Ma5．5）可以有效提高非设计点低马赫数时进气道的流量系数，从而提高超燃冲压发动机的非设计状态低马赫数推进性能；选择适当进气道侧板豁口后掠角度，又能保证低马赫数时进气道能够自起动，同时高马赫数时的发动机性能也能够基本保持，适当减小封口马赫数的进气道能够满足宽马赫数范围工作要求。

英文摘要：

It is difficult to maintain high performance over a wide range of Mach numbers for a hypersonic inlet.An osculating curved cone waverider inlet is designed and the design point of the inlet is optimized to obtain high performance with Mach numbers ranging from 4.5 to 6.From the numerical simulation and experiment results,it is found that the inlet mass flow capture ratio and the engine thrust can be efficiently improved by adjusting shock on lip Mach Number from 6 to 5.5,while the inlet can be guaranteed to be self-started by optimizing the inlet sweepback an-gle of the sidewalls.The experiment shows that the designed scramjet engine performance is im-proved under off-design conditions.