Abstract
Abstract : The investigation makes a direct comparison of cylindrical shell panel flutter boundaries obtained analytically with recent experimental boundaries reported in the literature. Further, an attempt was made to explain the discrepancies of the comparison through refinements of some structural aspects of the analysis. The non-linear Donnell shell theory is utilized together with the first-order, high Mach number approximation to the linear potential flow theory. The axisymmetric pre-flutter deformation, due to internal pressurization and axial loading of the shell in the presence of an air stream, is included in the analysis as the configuration about which the shell flutters. The structural boundary conditions assumed for the flutter state are the simply-supported, zero-traction boundary conditions as well as the classical, simply-supported boundary conditions. The problem associated with the pre-deformation state of the shell was solved exactly, whereas the approximate technique due to B. G. Galerkin was employed to solve the linearized system of flutter equations. In general, it is shown that agreement exists between the theory and experiment only in the region of small amounts of static loading of the shell.
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