Among the flutter phenomena that occur in low-speed incompressible flow, couple-mode flutter and stall flutter are probably the most widely investigated. Previous studies have found that flutter is mainly caused by the interaction of elastic structures and aerodynamic forces. When the blowing excitation is strong enough, stall flutter can be completely suppressed within several cycles.įlutter is a common aeroelastic phenomenon that affects the performance of various airfoil structures such as flexible wings, helicopter blades, and propellers. During pitching-down of the airfoil, leading-edge blowing induces rapid recovery of the aerodynamic moment, which promotes the decay of stall flutter. Low-momentum injection promotes shedding of dynamic stall vortices (DSVs) and reduces aerodynamic moment fluctuation, whereas high-momentum injection further suppresses the formation of DSVs and shrinks the aerodynamic moment hysteresis loop. The unsteady aerodynamic moment and flowfield results show that the leading-edge blowing effectively controls dynamic stall during oscillations. Time-resolved particle image velocimetry (TR-PIV) measurements are acquired to observe the flowfield evolution during stall flutter. It is found that the leading-edge blowing changes the local bifurcation behavior from a subcritical Hopf bifurcation followed by a saddle–node bifurcation to a supercritical Hopf bifurcation, with the flutter amplitude decreasing and the flutter critical velocity increasing. The dynamic responses are measured to analyze the nonlinear characteristics of the aeroelastic system. In this article, steady blowing from the leading edge is designed to suppress stall flutter of a two-dimensional airfoil model at 15 ° static equilibrium angle of attack. Stall flutter is a classical aeroelastic phenomenon that seriously affects the performance of flexible wings at high angle of attack.