SUPERSONIC FLUTTER ANALYSIS OF CLAMPED SYMMETRICAL COMPOSITE PANELS USING SHEAR DEFORMABLE FINITE-ELEMENTS

Abstract

THE flutter analysis of composite panels in supersonic flow has been performed by the finite element method based on the first-order shear deformable theory. The computational results of the vibration and flutter analysis agree well with the results given in the available references. Flutter boundaries have been obtained for both cross-ply and angle-ply composite plates. Also, the flutter analysis has been performed for both rectangular and trapezoidal plates with clamped edges. The plate aspect ratio, flow direction, and fiber orientation affect greatly the flutter boundaries.