Drag/Weight Reduction Using Split-Tip Winglet for TRA2012A Model
2020 年 63 巻 3 号 p. 69-79
詳細
2020 年 63 巻 3 号 p. 69-79
In this paper, we describe shape optimization of a split-tip winglet (STW) model for the TRA2012A commercial jet aircraft model. The STW configuration is expressed by attaching a small wing under the main winglet. The onboard fuel weight, main wing structure weight and the sum of these weights are objective functions, and are minimized respectively in a fixed aircraft operating range for the present optimization. The onboard fuel weight and main wing structure weight are respectively estimated from the aerodynamic drag obtained using computational fluid dynamics simulations and from an estimation formula based on aerodynamic force acting on the main wing. A Kriging response surface model approach is used as the optimization method. Finally, non-dominated optimal designs obtained using this optimization method are investigated in detail based on the variation in aerodynamic drag and the main wing structure weight. In the STW design having minimum total weight, a reduction in onboard fuel weight and increase in main wing structure weight are observed, and it is found that the reduction in onboard fuel weight per unit volume of STW is the largest.
