A static aeroelastic analysis of load redistribution and control surface reversal in subsonic and supersonic speeds has been performed for the tapered backward swept wing with 45° leading edge sweep angle. Both isotopic aluminium wing and T300/5208 Graphite/Epoxy composite wing are examined to see wing flexibility effect on the aerodynamic characteristics. This analysis uses two methods. One is the finite element method (F.E.M.) for the plate structural analysis and the other is the Gustavsson program based on Woodward panel method for the aerodynamic analysis. Two programs are related by a surface spline interpolation procedure. The final deformed shape of wing due to applied aerodynamic forces is determined by iterative manner using FEM and Gustavsson program. This study is discussed for the effect of compressibility and wing flexibility on the wing deformation and aerodynamic coefficients in supersonic speed. Also the wing with control surface has been analyzed. The wing deformation and aerodynamic coefficients are greatly affected by the fiber orientation of the composite wing. The appropriate fiber orientation can prevent control surface reversal.
