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- W3143961710 abstract "Adaptive wing can significantly enhance aircraft aerodynamic performance, which refers to aerodynamic and structural optimization designs. This paper introduces a two-step approach to solve the interrelated problems of the adaptive leading edge. Inthe first step, the procedure of airfoil optimization is carried out with an initial configuration of NACA 0006. On the basis of the combination of design of experiment (DOE), response surface method (RSM) and genetic algorithm (GA), an adaptive air-foil can be obtained whose lift-to-drag ratio is larger than the baseline airfoil's at the given angle of attack and subsonic speed.The next step is to design a compliant structure to achieve the target airfoil shape, which is the optimization result of the previous step. In order to minimize the deviation of the deformed shape from the target shape, the load path representation topology method is presented. This method is developed by way of GA, with size and shape optimization incorporated in it simul-taneously. Finally, a comparison study with the Solid Isotropic Material with Penalization (SIMP) method in Altair OptiStruct is conducted, and the results demonstrate the validity and effectiveness of the proposed approach." @default.
- W3143961710 created "2021-04-13" @default.
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- W3143961710 date "2013-01-01" @default.
- W3143961710 modified "2023-09-24" @default.
- W3143961710 title "Multidisciplinary design optimization of adaptive wing leading edge" @default.
- W3143961710 hasPublicationYear "2013" @default.
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