Abstract: Abstract A method to predict the aerodynamic characteristics of rotor with advanced ratio up to 0.8 is proposed. An aerodynamic model is established for the high advanced ratio rotor with the compressibility of advancing blade, stall effect and large reverse flow region of retreating blade as well as great sweep flow on the blade. A time-vary and non-uniform induced velocity model and unsteady flap motion model of blade are set up to adapt to the rotor aerodynamic model. A computational method of dynamic response for predicting the aerodynamic characteristics of high advanced ratio rotor was developed based on the inherent coupling relationship among rotor aerodynamics, rotor induced velocity and blade flap motion. Finally, H-34 rotor is taken to calculate its aerodynamic characteristic with various combinations of advanced ratio and rotor attack angle and the results are compared with the wind tunnel test data. The results show that the method can predict the aerodynamic characteristic of high advanced ratio rotor reasonably.