The invention relates to the technical field of aviation, in particular to an aircraft wake flow adjusting device for accelerating wingtip vortex dissipation, which comprises two adjusting sheets, and the two adjusting sheets are symmetrically mounted at the rear edges of wings on two sides of an aircraft close to wingtips; the adjusting piece is a rectangular block, the upper surface of the longitudinal section of the adjusting piece is linear or concave, and the lower surface of the longitudinal section of the adjusting piece is convex downwards. The adjusting sheet can generate a pair of small vortexes which are opposite to the main vortex in direction and low in strength by generating the pressure difference that the upper surface pressure is larger than the lower surface pressure, and the small vortexes and the main vortex form a reverse four-vortex system to excite instability of wake flow so that the wake flow can be rapidly dissipated.
本发明涉及航空技术领域,具体涉及一种用于加快翼尖涡耗散的飞机尾流调整装置,包括调整片,设有两个调整片用于对称安装于飞机两侧机翼后缘靠近翼尖处;调整片为矩形块,调整片的纵剖面上表面呈线形或内凹形,调整片纵剖面的下表面呈下凸形。本发明所设计的调整片通过产生上表面压力大于下表面压力的压力差,进而能够产生一对与主涡方向相反、强度较弱的小涡,与主涡一起构建出反向四涡系统,用以激发尾流的不稳定性,使得尾流快速消散。
Aircraft wake flow adjusting device for accelerating wingtip vortex dissipation
一种用于加快翼尖涡耗散的飞机尾流调整装置
18.05.2021
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |
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