| 摘要 |
An engine nacelle of an aircraft, which engine nacelle on one side comprises several fin-shaped vortex generators (3, 4, 5) so that with an increase in the angle of attack, to improve maximum lift, the field of vorticity generated by said vortex generators (3, 4, 5) overall extends over an increasing region of the wing in the direction of the wingspan, with the first vortex generator being located within a positioning corridor (K31) situated between two boundary lines (51, 52), wherein: the starting point (51 a) of the first boundary line (51) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 35 degrees and the engine-nacelle longitudinal coordinate X = L/4; the end point (51 b) of the first boundary line (51 ) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 25 degrees and the engine-nacelle longitudinal coordinate X = L·2/3; the starting point (52a) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4; the end point (52b) of the second boundary line (52) is the circumferential point of the engine nacelle with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L·2/3. |
