５つの山頂部をもつ平板コルゲート翼の翼表面圧力特性

抄録

A two-dimensional unsteady numerical analysis of a corrugated airfoil was performed to clarify the variation of flow around the airfoil as a function of leading-edge angle. A corrugated airfoil with five crests was made to follow the outline of NACA4412, and three types of airfoils with leading edge angles of 25° and 35° were selected as the target airfoils. The Reynolds number was set to 1.0 × 10⁴. Comparison of NACA4412 and the three types of corrugated blades showed that the lift coefficient was highest for NACA4412 at angles of attack of 4° or less and was significant for the corrugated blades at angles of attack higher than that. On the other hand, the drag coefficient was the lowest for NACA4412 at all angles of attack. Comparison of corrugated blades with different leading-edge angles revealed that at low angles of attack of 6° or less, the circulating flow in the first valley has a greater effect on aerodynamic characteristics than that in the second valley. On the other hand, at high angles of attack of 10° or more, flow cancellation was observed from the leading edge to the first crest of the upper surface of the wing, which is one of the reasons for the improved wing characteristics.