Firstly

the unsteady aerodynamic model of the airfoil with trailing-edge flap was developed.Secondly

the finite state wake model of electrically controlled rotor(ECR) based on the Peters-He generalized dynamic wake theory was developed

in which the effect of the trailing-edge flap on the rotor aerodynamic environment was considered.Combined with the relationship among the blade flapping angle

the blade pitch and the deflection angle of the trailing-edge flap

the model of calculating the aerodynamic characteristics of ECR was established finally.Then

wind tunnel tests were conducted

in which the aerodynamic force

the blade pitch

the deflection angle of the trailing-edge flap and the blade flapping angle varying with different test statuses were measured.Theoretical results basically coincided with the experimental data

which verified the correction of the theoretical model. Conclusions are drawn as follows: with the fixed rotor speed

there is a linear relationship between blade pitch response and flap control; rotor thrust decreases with the increase of flap collective control

and actual aerodynamic efficiency of the flap decreases under large collective control; in forward flight

flap collective control can cause changes of blade cyclic pitch.