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发明授权
CN107074350B 一种用于飞行器的机翼以及包括这种机翼的飞行器 有权

一种用于飞行器的机翼以及包括这种机翼的飞行器
摘要：
描述并示出了一种用于飞行器(1)的机翼(3)，包括主翼(7)和翼尖装置(9)，其中翼尖装置(9)的前叶片(21)和后叶片(27)以发散方式从附接端(19)向外延伸，其中当沿翼弦方向(33)观察时，前叶片前缘(23)在后叶片前缘(29)的前面延伸，并且前叶片后缘(25)在后叶片后缘(31)的前面延伸，其中在前叶片尖端(35)处所述前叶片(21)以与在后叶片尖端(37)处的后叶片(27)不同的上反角(ν)延伸，其中所述前叶片前缘(23)和所述前叶片后缘(25)以及所述后叶片前缘(29)和所述后叶片后缘(31)都具有切线连续的形状。本发明的目的是提供一种用于飞行器的机翼，其中对于预定的跨度尺寸，可以显著地减小诱导拖拽阻力，所述目的通过所述前叶片前缘(23)相对于机翼前缘(11)成切线连续地延伸、所述后叶片后缘(31)相对于所述机翼后缘(13)成切线连续地延伸、并且在沿翼弦方向(33)观察时所述前叶片后缘(23)至少部分地在所述后叶片前缘(29)之后延伸而得以实现。
摘要（英）：

Described and illustrated is a wing (3) for an aircraft (1), comprising a main wing (7) and a wing tip device (9), wherein a front blade (21) and a rear blade (27) of the wing tip device (9) extend away from an attachment end (19) in a diverging manner, wherein a front blade leading edge (23) extends in front of a rear blade leading edge (29) and a front blade trailing edge (25) extends in front of a rear blade trailing edge (31), when viewed in a chord direction (33), wherein at a front blade tip (35) the front blade (21) extends under a different dihedral angle (v) than the rear blade (27) at a rear blade tip (37), wherein the front blade leading edge (23) and the front blade trailing edge (25), as well as the rear blade leading edge (29) and the rear blade trailing edge (31) all have a tangent-continuous developing. The object of the present invention, to provide a wing for an aircraft, wherein for a predetermined span dimension the induced drag can be significantly reduced, is achieved in that the front blade leading edge (23) extends tangent-continuously with the wing leading edge (11), and the rear blade trailing edge (31) extends tangent-continuously with the wing trailing edge (13), and the front blade trailing edge (23) at least partially extends behind the rear blade leading edge (29), when viewed in the chord direction (33).

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