Abstract: To explore performance potential of hypersonic curved shock compression，high performance curved shock compression design results were obtained through multi-objective optimization and sampling computation，and were compared with traditional compression，under both inviscid and viscous condition. The results show that，(1)under inviscid condition，in the Pareto solutions of Multi-objective optimization，there exist curved shock compression cases，which have shorter length，higher compression efficiency and higher mass capture ratio under low flight Mach number，than traditional equal shock strength three ramps compression; (2)under viscous condition，when pressure ratio is 8.29(1±0.5%)，compared with isentropic compression，the length of curved compression is 35% shorter; compared with traditional equal shock strength three ramps compression，the length of curved compression is 8% shorter，the total pressure ratio is approximately equal，and the mass capture ratio under flight Mach number of 4 is 6% higher; compared with ramp-isentropic compression，the total pressure ratio of curved compression is 1.1% lower，while the mass capture ratio under flight Mach number of 4 is 6% higher; outlet boundary layer thickness and shape factor of curved shock compression are lower than those of other compression methods.

Key words: Hypersonic inlet；Curved shock compression；Gas-dynamic inverse design；Multi-objective optimization

摘要： 为了探索弯曲激波压缩流场性能所能达到的范围，分别在无粘和粘性条件下，通过多目标优化设计和抽样计算获取了高性能弯曲激波压缩方案，并与传统的压缩方式进行了对比。研究结果表明:(1)无粘条件下流场多目标优化Pareto最优解集中存在长度、压缩效率、低马赫数流量系数等性能参数均优于等激波强度三楔压缩的方案；(2)粘性条件下压比均为8.29(1±0.5%)时，弯曲激波压缩流场与等熵压缩流场相比，长度缩短了35%；与等激波强度三楔压缩流场相比，长度缩短了8%，总压恢复系数大小相当，来流马赫数4时流量系数高6%；与斜楔-等熵压缩相比，总压恢复系数仅相差1.1%，而来流马赫数4时流量系数提高了6%；其出口截面附面层厚度、附面层形状因子均低于其他压缩方式。

关键词: 高超声速进气道；弯曲激波压缩；气动反设计；多目标优化