翼の平面形が流線と等圧線の交差角に与える影響について

Abstract

Boundary layer separation reduces wing performance. The spanwise pressure gradient generates spanwise flow in boundary layer and increases boundary layer thickness. This thick boundary layer tends to separate easily. Therefore the zero pressure gradient normal to the streamlines could improve wing performance. In this research the effects of wing planform on intersecting angles of streamline and isobar are presented using boundary element method. The wing planforms which have little separation at large lift coefficient are studied.