头部进气的吸气式高超声速飞行器巡航状态多保持特定攻角飞行，导致常规不考虑攻角设计的三维内转进气道长时间工作于非设计攻角下，进气道性能下降明显。为此，将局部偏转吻切方法由外流进一步拓展至内流，提出了考虑巡航攻角的三维内转进气道设计方法。该方法将内转进气道分成激波决定段与压力分布决定段两部分，通过同时指定入射激波曲面和各流面内沿程压力分布，实现了给定来流攻角条件下的全三维内收缩流动的快速逆向求解。研究结果表明，基于该方法设计的进气道能够在来流马赫数6、高度27 km、4°巡航攻角的条件下较为精准地复现预设计激波与内收缩流场，进气道激波封口特性良好，实现全流量捕获。与常规不考虑攻角设计的进气道相比，考虑攻角设计的内转进气道在保证压缩性能基本一致的情况下，无黏流量捕获系数提升1.94%，喉道处无黏总压恢复系数提升6.56%。考虑黏性后，流量捕获系数提升1.90%，喉道处总压恢复系数提升6.69%，而隔离段出口的总压恢复系数则提升7.13%。

Air-breathing hypersonic vehicles with the head intake system typically cruise at a specific angle of attack for higher lift-to-drag characteristics. However， this can cause the 3D inward-turning inlet， designed without considering the angle of attack， to operate at off-design conditions for extended periods， which results in a noticeable decline in inlet performance. To solve this problem， the Local-Turning Osculating Cones （LTOCs） method is extended from external flow to internal flow， and a 3D inward-turning inlet design method considering the cruising angle of attack is then proposed. In this method， the inward-turning inlet is divided into the shock-based and pressure-based segments， derived by specifying the incident 3D shock wave and the streamwise wall pressure distributions in each stream surface respectively. Numerical results demonstrate that the proposed method can accurately reproduce the preassigned shock waves and internal flowfield at Mach number 6， 27 km altitude， and 4° angle of attack， resulting in full mass flow capture. Compared with the inlet design without considering the angle of attack， the design considering the cruising angle of attack can improve the inviscid mass-flow-capture coefficient and the inviscid total pressure recovery coefficient at the throat section by 1.94% and by 6.56%， respectively， when the compression performances of two inlets are essentially identical. Under the viscous conditions， the mass-flow-capture coefficient is augmented by 1.90%， the total pressure recovery coefficient at the throat section is enhanced by 6.69%， and the total pressure recovery coefficient at the isolator’s exit section is elevated by 7.13%.