A wind tunnel test was performed for active flutter suppression of a two-dimensional wing model by controlling the rotation of aileron in the use of D.C. servomotor as an actuator. The location of center of gravity, the frequency ratio and the mass ratio of the test model were at 40% chord length, 0.36 and 64, respectively. The experimental results showed that about 37% increase in flutter speed by feedback of the rotation angle and about 57% increase by feedback of the rotation angle and the translation were achieved. Furthermore, in the case of combined feedback of the rotation, its velocity and the translation no flutter was encountered even at 30m/s, i.e. the maximum speed of the wind tunnel that was two times of the open loop flutter speed. The test results were in good agreements with theoretical values which were calculated by taking the response characteristics of the actuator system and the reaction of actuator torque to the model into consideration.