为了预估高涵道比涡扇发动机飞行性能,使用GasTurb 11软件的试车数据分析功能计算出了某高涵道比涡扇发动机地面试车点与设计点各部件效率和流路损失的偏差.通过非设计点敏感性分析确定设计点与地面试车点的效率与损失偏差的相关性,最后预估得到高涵道比涡扇发动机的飞行性能.对某高涵道比涡扇发动机飞行性能预估研究表明:该方法切实可行,其中地面试车数据分析、地面和设计点偏差关系图、以及非设计敏感性分析是预估高涵道比涡扇发动机飞行性能的3个关键环节。 In order to estimate the flight performance of the turbofan engine with high bypass ratio, the deviation of efficiency and flow path loss of each high-bypass ratio turbofan engine ground test point and the design point was calculated by using the test data analysis function of GasTurb 11 software. The correlation between the design point and ground test point’s efficiency and loss deviation was determined by sex analysis and finally the flight performance of high bypass ratio turbofan engine was estimated.The research on the prediction of the flight performance of a high bypass ratio turbofan engine shows that this method is feasible, Among them, ground test data analysis, ground and design point deviation diagram, and non-design sensitivity analysis are the three key steps to predict the high-bypass ratio turbofan engine flight performance.