Abstract
A mathematical formulation and an algorithm for its numerical implementation are presented, intended to study the aeroelastic stability of cylindrical shells of arbitrary cross-section. The problem is solved in a three-dimensional formulation using the finite element method. The reliability of the results obtained is confirmed by comparison with the known solutions for circular shells. The dependences of the static pressure in an undisturbed gas flow, at which the loss of stability occurs, obtained for different ratios of the ellipse semiaxes and variants of the kinematic boundary conditions are analyzed. The possibility of increasing the boundaries of the aeroelastic stability of a cylindrical shell with an elliptical cross-section in comparison with a circular configuration in the case of cantilever fastening is demonstrated.
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