Supersonic flutter of a thermally stressed flat panel with uniform edge loads

Abstract : The effect of a nonuniform, self-equilibrating stress state associated with a parabolic temperature distribution is included in the flutter analysis of a rectangular, simply supported panel subjected to airflow over one surface and uniform edge loads. Linearized, static, two-dimensional aerodynamics is used in conjunction with thin-plate theory to formulate the problem. A Numerical results for a square panel show that nonuniform self-equilibrating stresses are as important as uniform stresses in affecting flutter behavior.