Abstract
This paper investigates the properties of the optimum structural design for supersonic flutter of the plate wing. The optimization method is based on the Evolutionary Structural Optimization method. In order to consider the properties of the optimum structural design, the optimum mass distribution, the optimum stiffness distribution and the optimum equivalent thickness distribution are compared in the numerical experiments. Numerical results show that the equivalent thickness distribution is the most suitable for the design variable of the structural optimization for the supersonic flutter. Numerical results also show that the optimum stiffness distribution has a relationship with the strain energy density of the 2nd flutter mode shape near the critical dynamic pressure.
