A parametric study on supersonic flutter behavior of laminated composite skew flat panels

Here, the system parameters effects on supersonic panel flutter behavior of laminated composite skew plates are investigated using a shear deformable finite element approach. The first-order high Mach number approximation to linear potential flow theory is employed for evaluating the aerodynamic pressure. The solutions of complex eigenvalue problem, formulated based on Lagrange's equation of motion are obtained using the standard method for finding eigenvalues. The variation of critical aerodynamic pressure is evaluated considering different parameters such as skew angle, fiber orientation, and boundary conditions. The influence of aerodynamic and structural damping, and thermo-mechanical loads on the critical aerodynamic speed is also examined.