Abstract: To develop a test method for the external drag of high bypass ratio civil aviation turbofan engine nacelle， the NACA-1 series asymmetrical nacelle tests were improved， and the test research of nacelle external drag has been finished in the 2.4m transonic wind tunnel which obtained the external drag of a certain type of high bypass ratio civil aviation turbofan engine nacelle， in the range of Mach number from 0.388 to 0.86. Finally， numerical simulation and experimental results were compared to verify the feasibility of the test method. The results show that the attack angle of the improved test scheme is extended from 0° of the original scheme to 0~4°，the variation of the test data of external drag has a good regularity when Mach number and mass flow coefficient change， the test results agree with the simulation results. The test method could be applied to the measurement of the external drag of high bypass ratio civil aviation turbofan engine nacelle.

Key words: Aviation engine;Nacelle;External drag;Wind tunnel test;Numerical simulation

摘要： 为了发展一种适用于大涵道比民用航空涡扇发动机短舱外部阻力的试验方法，对NACA-1系列轴对称短舱试验进行改进，并在2.4m跨声速风洞中完成了试验研究，获取了某型大涵道比民用航空涡扇发动机短舱在马赫数0.388~0.86的外部阻力，通过数值仿真与试验结果对比，验证了试验方案的可行性。结果表明，经过改进的试验方案的攻角适用范围由原方案的0°扩展致0°~4°，外部阻力随马赫数及流量系数的试验数据变化规律良好，试验结果与仿真结果吻合，试验方案适用于民用大涵道比航空涡扇发动机短舱外部阻力测量。

关键词: 航空发动机;短舱;外部阻力;风洞试验;数值仿真