Abstract
This paper investigates the structural optimization of plate wing for supersonic flutter. The optimization is performed to improve the critical dynamic pressure of the wing model by extending the Evolutionary Structural Optimization method. A delta wing with elastic plate is considered for the analysis model. The objective function is the difference between the variation of the first and second eigenfrequency in the vicinity of the critical dynamic pressure. Numerical results show that the critical dynamic pressure has been improved by the proposed optimization procedure.
