Smart Wing Stall Flutter Alleviation

One of the classical aeroelastic phenomena seriously affecting the performance of flexible wings at high angles of attack is stall flutter. This work shows how the stall flutter phenomenon can be alleviated and eliminated using a small inductor by implementing a piezoelectric patch. The dynamic responses are calculated to analyze the nonlinear characteristics of the aeroelastic system. A parametric study has been performed for different parameters. The main contribution of this work is to present a way to alleviate or eliminate the stall flutter on a regular two-dimensional (2D) wing by using a passive aeroelastic control, including piezoelectric patches and shunt circuits in which the size of the required inductance is small. The results indicate a considerable improvement in the dynamic aeroelastic behavior of a 2D wing.