直交格子流体ソルバと粒子法による柔軟膜翼に対する流体-構造連成計算

抄録

Flexible membrane wings, which could passively deform their shape owing to the aerodynamic forces distributions around the wing, have been considered for use in Mars exploration aircraft wing. In this study, coupled aerodynamic-structural calculations of flexible membrane wings with different material properties were performed to investigate the effects of these differences on aerodynamic performance. As a result, a larger deformation was observed in the softer elastic membrane. When flow separation is observed on the upper surface of the wing, a smaller modulus shifts the reattachment position toward the leading edge, resulting in a reduced deceleration area, which affects the drag coefficient. When the elasticity was too small, the drag force was found to increase due to excessive camber formation.