The invention discloses a commercial aircraft supercritical large sweepback wing which comprises a wing body, a bump string is arranged on the upper surface of the wing body in the wingspan direction, and the bump string comprises a plurality of bumps; the lift-drag ratio of an aircraft wing is increased by a bump mounted near the apex of the upper wing surface of the aircraft wing. According to the strength and position of the shock wave at different positions of the wing, the shock wave can be accurately controlled through the bump device which is designed based on aerodynamics and has different geometric parameters. Along with the change of the angle of attack of the wing, the thickness of the wing is increased by the bumps when no shock wave exists, and the lift force is improved; when a weak shock wave appears, the shock wave is weakened by the geometrical configuration, and finally the lift-drag ratio of the wing is improved.
本发明公开了一种商用飞机超临界大后掠机翼,包括机翼本体,所述机翼本体的上表面沿着翼展方向设置有一串鼓包串,所述鼓包串包括多个鼓包;通过安装在飞机机翼上翼面顶点附近处的鼓包提升机翼的升阻比。每个鼓包根据激波在机翼不同位置处的强度和位置,通过基于空气动力学设计的几何参数均不同的鼓包装置可以准确的控制激波。随着机翼迎角的变化,在无激波时,鼓包增加了机翼厚度,提升了升力;当出现弱激波时则由其几何构型弱化激波,最终实现机翼升阻比的提升。
Supercritical large sweepback wing of commercial aircraft
一种商用飞机超临界大后掠机翼
2024-03-22
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Variable sweepback wing structure for aircraft and aircraft
European Patent Office | 2024
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