The invention relates to a medium-Reynolds-number single-section airfoil profile suitable for general-purpose airplanes and unmanned aerial vehicles. The airfoil profile is obtained by evolutionary optimization by adopting a computational fluid mechanics method and a CST parameterization method on the basis of an original airfoil profile; the radius of the leading edge of the airfoil is 1.15% C, the maximum thickness of the airfoil is 15.00% C, the maximum thickness position is 31.13% C, the maximum camber of the airfoil is 4% C, and the maximum camber position is 43.70% C; wherein C is the chord length. Compared with an original airfoil profile, the resistance coefficient of the airfoil profile is lower under the same lift coefficient, and meanwhile the corresponding lift-drag ratio is also increased; and the performance is more excellent in a set lift coefficient range.
本申请涉及一种适用于通用飞机和无人机的中等雷诺数单段翼型。所述翼型是在原始翼型的基础上采用计算流体力学方法和CST参数化方法进化优化得到的;翼型的前缘半径为1.15%C,翼型的最大厚度为15.00%C,最大厚度位置为31.13%C,翼型的最大弯度为4%C,最大弯度位置为43.70%C;其中C为弦长。较原始翼型在相同升力系数下翼型的阻力系数更低,同时相应的升阻比也有提升;在设定升力系数范围内性能更优异。
Medium Reynolds number single-section airfoil profile suitable for general-purpose airplanes and unmanned aerial vehicles
适用于通用飞机和无人机的中等雷诺数单段翼型
2024-06-14
Patent
Electronic Resource
Chinese
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