The invention discloses a high-thrust high-lift-to-drag-ratio propeller and a design method of propeller blades of the high-thrust high-lift-to-drag-ratio propeller, the high-thrust high-lift-to-drag-ratio propeller comprises a hub and a plurality of blades connected with the hub, each blade comprises a plurality of section airfoils from a blade root to a blade tip, the radius of each blade is R, and at the position 0.25 R away from the center of a blade rotating disc, the radius of each blade is R; the attack angle of each paddle is 19-21 degrees, and the chord length of each paddle is 0.174 R; at the position 0.40 R away from the center of the paddle rotating disc, the attack angle of the paddle ranges from 16 degrees to 19 degrees, and the chord length of the paddle is 0.159 R; at the position 0.55 R away from the center of the paddle rotating disc, the attack angle of the paddle ranges from 14.2 degrees to 16.2 degrees, and the chord length of the paddle is 0.140 R. According to the high-thrust high-lift-drag-ratio propeller, the force effect of the propeller is higher than that of a traditional propeller at the same rotating speed, the efficiency of an aircraft can be improved, and the endurance time of the aircraft is prolonged.
本发明公开了一种大推力高升阻比螺旋桨及该螺旋桨桨叶设计方法,所述大推力高升阻比螺旋桨包括轮毂以及与轮毂连接的多片桨叶,所述桨叶包括从桨根到桨尖的多个的截面翼型,桨叶的半径为R,在距离桨叶旋转盘中心0.25R处,桨叶的迎角为19°~21°,桨叶的弦长为0.174R;在距离桨叶旋转盘中心0.40R处,桨叶的迎角为16°~19°,桨叶的弦长为0.159R;在距离桨叶旋转盘中心0.55R处,桨叶的迎角为14.2°~16.2°,桨叶的弦长为0.140R。本发明所公开的大推力高升阻比螺旋桨在相同转速下,该螺旋桨的力效要高于传统桨,能提升飞行器的效率,增加飞行器的续航时间。
High-thrust and high-lift-drag-ratio propeller and design method of propeller blades of high-thrust and high-lift-drag-ratio propeller
一种大推力高升阻比螺旋桨及该螺旋桨桨叶设计方法
2022-03-25
Patent
Electronic Resource
Chinese
Propeller thrust and drag in forward flight
IEEE | 2017
|Engineering Index Backfile | 1928
|NTIS | 1956
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