Abstract
A finite element approach to panel flutter problem has been attempted in this analysis. A method to derive the aerodynamic influence coefficient matrices kinematically consistent with the stiffness and inertia matrices, has been suggested. These matrices have been employed in the formulation of the dynamic equations of motion and the system of equations solved for their complex eigen values and vectors by the usual methods. This approach is general and is applicable to any boundary conditions. Some examples have been worked out, on a computer, for simply supported panels in supersonic flow and the results found to be in good agreement with those from other conventional methods.
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