The paper presents a theoreticla analysis and an experimental study of blade flutter suppression by means of active acoustic excitation. In the theoretical analysis, a linearized mathematical method to calculate the aerodynamic force and work on an osicillating airfoil interacting with sound wave generted from a lud-speaker mounted at a wall surface of a wind tunnel is formulted. Dependence of the suppression effect on the location, width of the actuator surface and the phase difference between the blade an actuator surface oscillations are investigated. Both theoreticla and experimental results show that the actuator surface oscillation mos efectively suppresses a coupled bending-torsional osicallation of the blade when the center fo the loud-speaker diaphragm is placed a quarter blade chord downstream from the leading edge of the blade. Furthermore a 12.5 increase in a criticla flutter velocity could be attained by the active control system.
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