This study describes the establishment of the necessary similarity conditions for dynamic aeroelastic stability of laminated composite plates. An analytical investigation based on the direct use of the governing equations of the systems is undertaken to derive the necessary scaling laws and similarity conditions. The method presented herein has already been shown to be effective in the design of scaled down models for buckling and vibration response of laminated composite shells and panels. In this study, the flutter speeds of the prototypes are predicted by projecting the flutter speed of the model using the derived scaling law. The results presented herein, indicate that, for flutter of composite plates, based on structural similitude, a set of scaling laws can be found, which are used to develop design rules for small scale models. Models with different material properties, thickness, fiber orientation, Mach number, aspect ratio, and number of plies than those of the prototype can predict the flutter behavior of the prototype with good accuracy.

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