In order to predict the flight performance of a high bypass ratio turbofan engine. Errors of component efficiencies and pressure losses of a high bypass ratio turbofan engine at ground test point and design point were estimated by using GasTurb 11 software. And then the relationships of the errors between design point and ground test point were determined through the non-design point sensitivity analysis method. In terms of the above relationships determined

the flight performance of the high bypass ratio turbofan engine can be predicted at last. Prediction of the flight performance of a high bypass ratio engine shows that the method is feasible

analysis of ground test data

relationships of delta value of ground point and design point and the non-design point sensitivity analysis are three key links in predicting the flight performance of high bypass ratio turbofan engines.