翼列開閉型モーフィング翼のサロゲートモデルに基づく多目的空力最適化と設計情報の抽出

抄録

To improve short takeoff and landing performance and stall characteristics of fixed-wing unmanned aerial vehicles, a Multi-Slotted Variable-Camber Morphing Wing was proposed. This airfoil is composed of five components connected, and the aerodynamic characteristics can be adjusted by changing the configuration of each airfoil. In this study, the arrangement of components of the morphing airfoil is optimized aerodynamically by defining 12 design variables, and the obtained Pareto solutions are analyzed to identify essential design variables and components to improve the aerodynamic performance of the entire airfoil. As a result, it was shown that the position of the fourth and fifth components is essential for the lift coefficient, the distance between components is essential for the drag coefficient. Moreover, the position of the second component is essential for the pitching moment coefficient.