The invention discloses a wing end standing vortex lift augmentation device which comprises a device upper surface, a device lower surface, a leading edge surface and a wing profile, a wing upper wing surface extends outwards to form the device upper surface, a wing lower wing surface extends outwards to form the device lower surface, and the extension length of the device upper surface is larger than that of the device lower surface. A distance exists between the upper surface and the lower surface of the device, and wingtips do not coincide with each other; the device upper surface, the device lower surface, the front edge surface and the airfoil profile jointly form a semi-closed cavity, when incoming flow exists in the semi-closed cavity, a wing end standing vortex rotating in the direction away from the central axis of the fuselage is formed in the semi-closed cavity, and the rotating direction of the wing end standing vortex is opposite to that of a wingtip vortex. According to the three-dimensional wing, airflow on the lower wing surface of the wing is prevented from flowing to the upper wing surface of the wing through the wing end standing vortex in the semi-closed cavity, so that the trend that the airflow on the lower wing surface of the wing is reversed upwards can be inhibited under the condition of not depending on physical obstruction, the lift force of the three-dimensional wing is effectively increased, and the induced resistance is reduced.
本发明公开了一种翼端驻涡增升装置,包括装置上表面、装置下表面、前缘面和翼型剖面,机翼上翼面向外延伸形成装置上表面,机翼下翼面向外延伸形成装置下表面,装置上表面的展长大于装置下表面的展长,装置上表面与装置下表面之间有距离,且在翼尖不重合;装置上表面、装置下表面、前缘面和翼型剖面共同形成半封闭式空腔,半封闭式空腔有来流时内部形成背离机身中轴线方向旋转的翼端驻涡,翼端驻涡的旋转方向与翼尖涡相反。本发明通过半封闭式空腔内的翼端驻涡来阻止机翼下翼面的气流流向机翼上翼面,从而在不依赖物理阻隔的条件下,可抑制机翼下翼面气流上反的趋势,有效地增加了三维机翼的升力,减小了诱导阻力。
Wing end standing vortex high lift device
一种翼端驻涡增升装置
2025-02-07
Patent
Electronic Resource
Chinese
IPC: | B64C AEROPLANES , Flugzeuge |
Lift-induced wing-tip vortex attenuation
NTRS | 1974
|Lift-induced wing-tip vortex attenuation
AIAA | 1974
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AIAA | 1973
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