The invention relates to a winglet (9) for an aircraft, comprising: a first control section (L1) located in a base region of the winglet (9); a third control section (L3) located in the tip region of the winglet (9); and a second control section (L2) located between the first control section (L1) and the third control section (L3). The second control section (L2) is a flow control section which is provided with a winglet slot (11) along at least one part of the spanwise direction of the winglet (9), and the first control section (L1) and the third control section (L3) are non-flow control sections. According to the winglet for the aircraft, flow separation of the winglet in a low-speed and large-attack-angle state can be delayed and the flight resistance in a high-speed cruise state can be reduced without designing a complex structure by virtue of the aerodynamic configuration of the winglet.
本发明涉及一种飞行器用翼梢小翼(9),包括:位于翼梢小翼(9)的基部区域的第一控制段(L1);位于翼梢小翼(9)的梢部区域的第三控制段(L3);以及位于第一控制段(L1)和第三控制段(L3)之间的第二控制段(L2)。第二控制段(L2)是流动控制段,其沿翼梢小翼(9)的展向的至少一部分开设有小翼开缝(11),而第一控制段(L1)和第三控制段(L3)为非流动控制段。上述飞行器用翼梢小翼借助其气动外形,无需设计复杂结构即能延缓低速大攻角状态下的小翼流动分离且降低高速巡航状态下的飞行阻力。
Winglet for aircraft and aircraft equipped with such winglet
飞行器用翼梢小翼和配备有该翼梢小翼的飞行器
2023-06-09
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
European Patent Office | 2019
|European Patent Office | 2021
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