Supersonic flutter characteristics of composite cylindrical panels

Supersonic panel flutter behavior of laminated composite plates and cylindrical panels are investigated here using a 16-noded isoparametric degenerated shell element. The first-order high Mach number approximation to linear potential flow theory is employed for evaluating the aerodynamic pressure. The solutions of the complex eigenvalue problem are obtained using the standard method for finding eigenvalues. The effects of curvature, laminate stacking sequence, air flow direction and boundary condition on the supersonic flutter characteristics of laminated composite cylindrical shell panels are investigated. The influences of thermal stress, as well as in-plane compressive and shear stresses on the critical aerodynamic speed are also examined.