عنوان مقاله [English]
A combination of the control surface to the wing section is carried out by mechanisms which usually have freeplay. This leads to structural nonlinearity behavior and, as a result, nonlinear aeroelastic behavior. In this study, the aeroelastic behavior of an airfoil with a control surface, which, together, have three degrees of freedom; i.e.: heaving and pitching of the airfoil and pitching of the control surface, has been analyzed in a subsonic incompressible flow regime. A bilinear spring is employed to joint the airfoil to the control surface and a quasi steady aerodynamic model is used for aerodynamic modeling. It is shown that the quasi steady aerodynamic model is not reliable for determination of the aeroelastic behavior and flutter boundary of the airfoil.
However, the aeroelastic characteristics of the airfoil can be investigated using such a modeling approach. As another outstanding outline, it is concluded that, often, the instability is of a Limit Cycle Oscillation (LCO) type.