The experimental investigation of static aeroelasticity for isotopic wings and composite wings has been demonstrated through a low-speed wind tunnel. Isotopic wing models are made of aluminum 5052 and classified into three types of wing which are forward swept, unwept, and backward swept wing. The models of composite wings are made of Graphite/Epoxy materials. The stacking sequence of composite wing is [$\theta_2/90_3$]s. Six different fiber orientations, $\theta$ are chosen in this wind tunnel models. As wind velocity increase, the aerodynamic coefficients (lift, drag coefficients) of the forward swept and the unwept wings increase due to the increase of local angle of attack of flexible wing. On the contrary, those of the backward swept wing decrease due to the decrease of local angle of attack. In the case of composite wing, lift, drag and twist of wing tip have the maximum values at 60° fiber orientation, and the minimum values at 120° fiber orientation. Bending deflection of wing tip has the maximum values at 0°, 30° fiber orientations, and the minimum values at 90°, 120° fiber orientations. The aerodynamic characteristics have been greatly affected by the wing swept angles and fiber orientation.
