A numerical procedure is presented for determination of optimal member sizes of aircraft structural components such that weight is minimized subject to a specified lower bound on flutter speed. The method has been devised to utilize the most general and accurate of current analytical flutter prediction methods so that substructures of arbitrary aerodynamic and structural complexity can be efficiently synthesized with substantial numbers of design parameters. Expressions for first-order flutter derivatives are developed for driving a gradient based mathematical program. Application to a sample problem of just two design variables is used to illustrate the method and the optimization of a larger problem is included to indicate favorable operational efficiency.
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GWIN et al. (1973) studied this question.
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