The invention discloses a wing broken vortex structure, a wing and an airplane, the wing broken vortex structure comprises a first opening formed in the front edge of an airplane wing body and a second opening formed in the rear edge of the airplane wing body, the first opening and the second opening are communicated through a communicating pipe, and the communicating pipe is located in the airplane wing body. Via the wing broken vortex structure, the front edge and the rear edge of the wing body are communicated through the communicating pipe; airflow blown to trailing vortex is generated inthe communicating pipe through the front-back pressure difference of the wing body. The trailing vortex is generated behind a wing tip of the wing body; the communicating pipe is located in the innerside of the wing tip, air flow guided out by the communicating pipe can apply lateral jet flow to the trailing vortex, the vortex loop amount is unbalanced, instability of the vortex can be effectively triggered, dissipation of the trailing vortex is greatly accelerated, influence of the trailing vortex on a rear machine is reduced, and the wing broken vortex is extremely simple in structure, quite convenient to manufacture, particularly good in effect and convenient to popularize.
本发明公开了一种机翼碎涡结构、机翼及飞机,该机翼碎涡结构包括设于飞机机翼本体前缘的第一开口和设于所述机翼本体后缘的第二开口,所述第一开口和所述第二开口通过连通管导通,所述连通管位于所述机翼本体内部。运用本发明所述的一种机翼碎涡结构,通过所述连通管导通所述机翼本体前缘和后缘,由所述机翼本体前后压力差在所述连通管中产生吹向尾涡的气流,由于尾涡产生于所述机翼本体翼梢之后,所述连通管位于翼梢内侧,所述连通管导出的气流能够向尾涡施加侧向喷流,使涡环量不均衡,可以有效触发涡流的不稳定性,极大加速尾涡消散,减小尾涡对后机的影响,该机翼碎涡结构极其简单,制造十分方便,效果特别良好,便于推广。
Wing broken vortex structure, wing and airplane
一种机翼碎涡结构、机翼及飞机
28.07.2020
Patent
Elektronische Ressource
Chinesisch
IPC: | B64C AEROPLANES , Flugzeuge |