The invention provides a subsonic high-lift low-resistance laminar flow airfoil for the middle of a helicopter blade. The radius of the front edge of the airfoil is 0.00588, the maximum thickness of the airfoil is 13.10%, the airfoil is located at the 30.5% chord length of the airfoil, the maximum camber is 0.0126, the airfoil is located at the 27.7% chord length of the airfoil, and the included angle of the rear edge of the airfoil is 6.78 degrees. And the radius of the leading edge, the maximum thickness and the maximum camber are described by adopting dimensionless dimensions, and the chord length c of the airfoil is taken as a reference. Compared with an NACA 62 (3)-213 classical laminar flow airfoil, the airfoil can push a transition position backwards, a larger laminar flow area is maintained, and the airfoil has a better lift-drag characteristic. And meanwhile, the raising moment can be balanced by increasing the bending degree of the airfoil, so that the airfoil has a lower pitching moment peak value compared with NACA 62 (3)-213.
本发明提出一种用于直升机桨叶中部的亚音速高升力低阻层流翼型,翼型前缘半径为0.00588,翼型最大厚度为13.10%,位于翼型30.5%弦长处,最大弯度为0.0126,位于翼型27.7%弦长处,后缘夹角为6.78°;所述前缘半径、最大厚度、最大弯度采用无量纲量进行描述,以翼型弦长c为基准。本发明相对于NACA 62(3)‑213经典层流翼型,其能够推后转捩位置,维持更大的层流区,具有更好的升阻特性。同时翼型弯度的增大能够平衡抬头力矩,使其较NACA 62(3)‑213具有更低的俯仰力矩峰值。
Subsonic high-lift low-resistance laminar flow airfoil profile for middle part of helicopter blade
一种用于直升机桨叶中部的亚音速高升力低阻层流翼型
2023-08-29
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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