Supersonic flutter analysis of thermally stressed laminated composite flat panels

This paper deals with supersonic flutter analysis of laminated composite panels exposed to a temperature field. The formulation includes transverse shear deformation, and in-plane and rotary inertia effects. The aerodynamic force is evaluated by Considering the first-order high Mach number approximation to linear potential flow theory. The solution for the complex eigenvalue problem is obtained by the QR algorithm. Before obtaining the critical aerodynamic pressure, thermal stress and buckling load are calculated. Numerical results are presented for both cross- and angle-ply laminates. A detailed parametric study is carried out to observe the effects of different temperature loadings, thickness, number of layers, lamination scheme and boundary conditions on the flutter boundary.