REDUCED-ORDER AERODYNAMIC MODEL AND ITS APPLICATION TO A NONLINEAR AEROELASTIC SYSTEM

Starting from a finite state model for a two-dimensional aerodynamic n ow over an airfoil, the eigenmodes of the aerodynamic now are determin ed. Using a small number of these aerodynamic eigenmodes, i.e., a redu ced-order model, the aeroelastic model is formed by coupling them to a typical section structural model with a trailing-edge flap. A free-pl ay nonlinearity is modeled. Results are shown from the finite state mo del, the reduced-order model, and previous theoretical and experimenta l work, All results are in good agreement.