A static aeroelastic load redistribution analysis has been performed for three dimensional aircraft wing with flap deflection in subsonic speed. Three dimensional wing consists of spars, ribs, and skin structure. The Gustavsson program based on Woodward panel algorithm was used to calculate the 3D wing aerodynamic load. For the structural analysis of three dimensional wing, a finite element program (D/ANALYZE) was used. The overall procedure is performed in an iterative manner using the surface spline method. This study is focused on investigating the effect of wing flexibility on the deformation and stress of 3D wing with control surface. Also, the effect of flap deflection upon the structural deformation and aerodynamic forces are discussed. The present analysis capability for the aerodynamic load redistribution of conventional 3D wing with control surface can be applied to the preliminary design of the aircraft wing. Also, the present capability developed here can be applied to the aerodynamic and structural analysis of the general 3D wing with control surface deflection.
