Abstract
The main aim of this work is to outline a forward swept wing (FSW) design problem for reducing the optimization time and cost. Dynamic mesh technique was used in the design of a transonic FSW by coupling it with heuristic algorithms. To obtain the initial FSW mesh from backward swept wing (BSW) domain, a modified dynamic mesh method has been developed. It is observed that the drag coefficient can be reduced by 15 percent while the lift coefficient is tried to be close to the design value determined at the beginning as a design constraint. The results are also compared to BSW results. Especially the taper ratio change direction differs from previous BSW optimization.
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