Abstract
Systems of equations are obtained to study the onset of panel flutter of a composite shell with a linearly varying thickness. Using a model developed, the critical flow-over speed, corresponding to the onset of flutter, as a function of thickness difference between the left and right ends of the shell is calculated for various values of the axial compressive force and shell length with and without considering its structural damping. The discrepancy between the critical flow-over speed calculated for the shell and a shell with the corresponding integrally average constant thickness is determined.
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