吸气式高速飞行器以超燃冲压发动机为动力，采用乘波体作为前体为进气道提供预压缩气流，前体的压缩能力对飞行器性能和超燃冲压发动机的性能起着决定性作用。乘波体的压缩性能与马赫数和激波角密切相关，单级压缩通常需要较大激波角才能满足进气道气流增压比的需求，同时也会引起前体气动性能降低，产生较大的抬头力矩和较低升阻比。为进一步提高乘波前体的压缩性能，提出了一种纵向分段的多级压缩乘波前体设计方法，可以根据进气道入口需求灵活调整压缩量和长度比例，且高压区主要聚集在乘波体出口中间位置，能够匹配宽范围的进气道，避免较大的边缘压力泄漏。基于该方法完成了多级压缩的程序开发，分别开展了锥导和吻切锥二级/三级压缩前体的设计与分析。数值结果表明，设计的多级压缩乘波体压缩能力显著提升，可同时满足高增压比、高总压恢复系数和高升阻比等设计需求，具有较好的工程应用前景。

The air-breathing high speed vehicle is powered by a scramjet and uses the waverider as a forebody to provide compressed airflow for the intake. The compressibility of the forebody plays a decisive role in the performance of the aircraft and scramjet. The compression performance of the waverider is closely related to the Mach number and shock angle. The single-stage compression usually requires a larger shock angle to meet the requirements of the intake airflow pressure-boost ratio， and meanwhile， the forebody aerodynamic performance is reduced with the larger pitching moment and lower lift-to-drag ratio. To further improve the compression ability of the waverider forebody， a longitudinally segmented multi-stage compression waverider forebody design method is proposed， which can flexibly adjust the compression amount and length ratio according to the inlet need of intake. The produced high pressure area is mainly concentrated in the middle position of the lower waverider surface， which can match a wide range of intake and avoid more edge pressure leakage. Based on the method， the design code is developed， and the two-stage and three-stage cone-derived and osculating-cone waveriders are designed and analyzed， respectively. The numerical results show that the designed waverider has significantly improved compressibility and can simultaneously satisfy the high static pressure， high total pressure recovery and high lift-to-drag ratio with good engineering application prospects.