The invention discloses a rotor wing of a rotorcraft and the rotorcraft. The rotor wing of the rotorcraft comprises blades and a propeller hub, the blades are installed on a driving assembly of the rotorcraft through the propeller hub, the wing section of each blade is composed of a front edge, a tail edge, an upper arc line and a lower arc line, and the upper arc line and the lower arc line are located between the front edge and the tail edge. The ratio a/c of the maximum thickness a of the airfoil of each blade to the chord length c of the airfoil is 6.85%, and the maximum thickness is located at the position where x/c is 30.5%; and the ratio b/c of the maximum camber b of the airfoil of each blade to the chord length c of the airfoil is 6.6%, and the maximum camber b is located at the position where x/c is 47.1%. The rotor wing obtained through the technical scheme has higher aerodynamic efficiency and lighter weight, and under the same lifting surface distribution design, the required rotating speed is lower, and a noise is lower.
本公开涉及一种旋翼飞行器的旋翼及旋翼飞行器,其中旋翼飞行器的旋翼,包括桨叶和桨毂,桨叶通过桨毂安装于旋翼飞行器的驱动组件上,桨叶的翼型由前缘、尾缘以及位于前缘和尾缘之间的上弧线和下弧线构成,桨叶的翼型的最大厚度a与翼型的弦长c之比为a/c=6.85%,最大厚度位于x/c=30.5%处;桨叶的翼型的最大弯度b与翼型的弦长c之比为b/c=6.6%,最大弯度b位于x/c=47.1%处。通过上述技术方案得到的旋翼具有更高的气动效率、更轻的重量,同样升力面分布设计下,所需转速更低,噪音更小。
Rotor wing of rotorcraft and rotorcraft
旋翼飞行器的旋翼及旋翼飞行器
2021-06-08
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |