Abstract
The objective of this study is to design a two-dimensional panel subject to transonic flutter constraints in the presence of an extreme thermal environment. The unsteady aerodynamic model is based on a high-order stabilized finite element formulation of the Euler equations. The linearized dynamic instability problem is converted into the flutter-stability problem, and an iterative procedure is used to identify the flutter velocity at a given design point. The design variables include the lengthwise thickness and density distributions, with the objective function as the minimization of structural mass. The first set of designs are obtained for an unstressed panel with flutter constraints at Mach 1.1 and Mach 2.0, and it is found that the optimal thickness distribution closely mimics the amplitude of the constraining flutter mode. The thermally stressed panel is designed for aeroelastic stability about the nonlinear static equilibrium. It is found that the optimum mass of the thermally stressed panels is lower than the optimum mass of the unstressed panels due to the additional stiffening from the transverse deformations.
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