Abstract
Abstract : The flutter of two-bay clamped-edge and simply supported panels at supersonic Mach numbers is studied to determine the influence of structural and aerodynamic coupling. It is found that the effect of structural coupling between the panel bays is unimportant both for the 'single-degree-offreedom' flutter modes that are critical at the lower supersonic Mach numbers and for the critical coupled flutter modes that develop at higher supersonic Mach numbers. The effect of aerodynamic coupling is found to be of importance for the 'single-degree-of-freedom' flutter modes only. Furthermore, the severity of this effect is highly dependent upon the panel boundary conditions. (Author)
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