Abstract: To investigate the matching principle between supersonic inlets and gas turbine engines and to improve the installed performance of supersonic propulsion systems，a simplified method to simulate the supersonic inlet installed performance in terms of engine and inlet matching was developed. This method was based on quasi one dimensional simulation of the flow field of supersonic inlets and the component-based gas turbine engine performance simulation model. Consequently，it is capable of simulating the installed drag of supersonic inlets on different flight and working conditions. This method was validated using data from other references before it was used to investigate the matching between ‘2+1’ supersonic inlet and a turbofan engine during subsonic cruise and the performance of a variable supersonic inlet. Results show that，the deviations of inlet pressure recovery and mass flow coefficient are within 1.4%，while the deviations of installed performance of some turbofan engine is within 9%. Noticeable additive drag was detected during subsonic cruise when the engine was working in deep throttle conditions. Variable inlet can reduce the spillage drag and increase the stability of supersonic inlet at high flight Mach numbers.

Key words: Supersonic inlet；Matching of inlets and engines；Additive drag；Spillage drag；Variable inlet

摘要： 为了研究超声速进气道与发动机的匹配特性，改善推进系统的安装性能，结合准一维进气道流场计算方法和基于部件法的发动机总体性能仿真模型，发展了一种考虑进发匹配的超声速进气系统安装性能快速计算方法。该方法能够计算不同飞行条件和不同进气道工况下，超声速进气系统的性能和安装阻力。利用文献中的数据对本文的模型进行了校核，并以两斜一正外压式进气道为例，研究了亚声速飞行时的附加阻力和进气道的调节方法。与文献中数据对比表明，进气道总压恢复和流量系数误差小于1.4%，发动机安装推力计算结果误差小于9%。超声速进气道在亚声速巡航状态下由于发动机节流带来较大的附加阻力，而进气道调节可降低高马赫数下的溢流阻力并增加进气道的稳定裕度。

关键词: 超声速进气道；进发匹配；附加阻力；溢流阻力；变几何进气道