The invention belongs to the technical field of helicopter aerodynamic design, and discloses a low-noise rotor blade aerodynamic configuration of a helicopter. The aerodynamic configuration of the blade adopts a multi-section airfoil configuration, a sweepback blade tip configuration, a blade tip sharpening and negative torsion design, so that the aerodynamic noise of the rotor wing can be effectively reduced. The blade and reference blade noise measurement test is carried out in an acoustic wind tunnel, and the result shows that in a typical oblique descending state, the blade noise is superior to that of the reference blade, the maximum rotor noise reduction amplitude reaches 6 decibels, and the average noise reduction amplitude is close to 4 decibels.
本发明属于直升机气动设计技术领域,公开了一种直升机低噪声旋翼桨叶气动外形。桨叶气动外形采用了多段翼型配置、前后掠桨尖构型、桨尖尖削以及负扭转设计,能够有效地降低旋翼气动噪声。在声学风洞开展了该桨叶和基准桨叶噪声测量试验,结果表明,在典型斜下降状态,该桨叶噪声优于基准桨叶,旋翼噪声最大降幅达6分贝,平均降噪幅度接近4分贝。
Low-noise rotor blade aerodynamic configuration of helicopter
一种直升机低噪声旋翼桨叶气动外形
2021-01-05
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
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