The aeroelastic response of a two-dimensional NACA 0012 airfoil in subsonic stalled flow is considered. The airfoil is flexibly mounted and structurally linear. A semi-empirical aerodynamic analysis, accounting for both pitch- and plunge-motion, is used to model the dynamic stall phenomena, resulting in nonlinear aerodynamic forces and moments. The aeroelastic response of the airfoil is obtained for both pure pitch-motion, as well as for the more general case where both pitch- and plunge-motion are allowed. In both cases self-excited oscillations are obtained, and apparently chaotic motion of the airfoil is predicted for certain combinations of airfoil parameters.
展开▼
