The invention relates to a fairing (26) for an aircraft flap mechanism, comprising: a fairing front section (32) located forward of a trailing edge of a wing of an aircraft; and a fairing rear section (33) located behind the trailing edge of the wing of the aircraft, the fairing front section (32) and the fairing rear section (33) bordering in the bottom region of the fairing (26) at a front-rear section junction point (P3), the height of the lowest point (P2) of the fairing rear section (33) being lower than or equal to the height of the front-rear section junction point (P3). Compared with the conventional fairing scheme, the fairing provided by the invention has the advantages that the lift loss is obviously reduced, the wing circular rector distribution in the flight state is also improved, and both the lift loss and the wing circular rector distribution result in the improvement of the aerodynamic efficiency.
本发明涉及一种用于飞行器襟翼机构的整流罩(26),包括:位于飞行器的机翼后缘前方的整流罩前段(32);以及位于飞行器的机翼后缘后方的整流罩后段(33),整流罩前段(32)和整流罩后段(33)在整流罩(26)的底部区域中交界在前后段交界点(P3)处,整流罩后段(33)的最低点(P2)高度低于或等于前后段交界点(P3)的高度。与常规的整流罩方案相比,采用根据本发明的整流罩不仅升力损失明显下降,飞行状态下的机翼环量分布也得以改善,两者均导致气动效率提升。
Fairing for aircraft flap mechanism
用于飞行器襟翼机构的整流罩
2024-05-28
Patent
Electronic Resource
Chinese
European Patent Office | 2018
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|European Patent Office | 2015
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