新一代先进隐身军机进气道出口会出现复杂的旋流/总压组合畸变，而国际上围绕航空发动机旋流/总压组合畸变试验评定方法还未达成共识。发展航空发动机旋流/总压组合畸变试验评定方法，支撑航空发动机安全运行边界的划定，是新一代先进隐身军机进气道/发动机气动相容性评定亟需解决的技术问题。针对旋流/总压组合畸变流场测试、畸变发生装置设计以及畸变指数定义，国内外积累了一定的技术基础，但仍需围绕大气流偏折角下稳/动态流场准确测试、复杂畸变图谱测点分布设计、畸变发生装置的高效设计与连续可调以及可反映发动机稳定性变化的畸变指数定义开展持续的技术攻关和研究工作。

Complex swirl/total pressure combined distortion occurs at the inlet exit of new-generation advanced stealth military aircraft. However, there is still no international consensus on the test and evaluation methods for swirl/total pressure combined distortion in aero-engines. Developing such test and evaluation methods for aero-engines to support the definition of safe operating boundaries of aero-engines is a critical technical issue that needs to be urgently addressed for the aerodynamic compatibility evaluation between the inlet and engine of new-generation advanced stealth military aircraft. Domestic and international entities have accumulated a certain technical foundation in areas such as swirl/total pressure combined distortion flow field testing, distortion generator design, and distortion index definition. Nevertheless, continuous technical research and development efforts are still required focusing on the following aspects: accurate steady/dynamic flow field testing under large flow deflection angles, 测点 distribution design for complex distortion profiles, efficient design and continuous adjustability of distortion generators, and the definition of distortion indices that can reflect changes in engine stability.