Abstract
A finite element method is developed for studying the supersonic flutter analysis of arbitrary skewed and cracked panels. The finite element method employs a 48 degrees of freedom general plate element based on tensorial mathematics and using classical lamination theory, and linearized piston aerodynamic theory. Finite element results are obtained for isotropic panels for which comparisons can be made for validation. The effects of fiber orientation and flow angle on the flutter characteristics are presented and discussed for selected examples to illustrate the behavior of flutter characteristics for composite cracked panels.
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