The invention relates to the field of propellers or rotors for airplanes, in particular to a low-noise rotor for a ducted vertical take-off and landing aircraft. The ducted low-noise rotor wing for the vertical take-off and landing aircraft comprises a ducted body (1), a support frame (21), a rotating shaft (22) and a rotor wing (3), and is characterized in that the rotor wing (3) is provided with a lower dihedral angle (31) and a sharp part (32), and the lower dihedral angle (31) is-5 degrees to-10 degrees; the sharpening ratio of the rotor wing (3) is 0.5-0.7; the diameter of the rotating surface of the rotor wing (3) is 2.1 R, the average chord length of the rotor wing (3) is 0.2 R, and the average thickness of the rear end of the rotor wing (3) is 0.04 R. Noise is effectively reduced, and lifting force is improved.
本发明涉及用于飞机的螺旋桨或旋翼领域,具体为一种用于涵道式垂直起降飞行器的低噪音旋翼。一种用于垂直起降飞行器的涵道式低噪音旋翼,包括涵道本体(1)、支撑架(21)、转轴(22)和旋翼(3),其特征是:旋翼(3)设有下反角(31)和尖削(32),下反角(31)为‑5°~‑10°;旋翼(3)的尖削比为0.5~0.7;旋翼(3)旋转面的直径为2.1R,旋翼(3)的平均弦长为0.2R,旋翼(3)后端的平均厚度为0.04R。本发明有效降低噪声,提升升力。
Low-noise rotor wing for ducted vertical take-off and landing aircraft
用于涵道式垂直起降飞行器的低噪音旋翼
2024-12-27
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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