Engine pod for an aircraft with a vortex generator arrangement

An engine pod for an aircraft that features a pod housing (19) with a first (S1) and a second (S2) side and several fin-like vortex generators (21, 22, 23;

• 31, 32) that are arranged on one side (S1, S2) of the pod housing (19) in such a way that the overall vorticity field generated by said vortex generators extends over an increasing airfoil area in the wingspan direction as the angle of attack increases in order to improve the maximum lift, wherein the foremost point of a first vortex generator (31) lies within a positioning corridor (K31) that is situated between two boundary lines (51, 52), wherein
• the point of origin (51a) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=35 degrees and the longitudinal engine pod coordinate X=L/4,
• the end point (51b) of the first boundary line (51) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=25 degrees and the longitudinal engine pod coordinate X=L·⅔,
• the point of origin (52a) of the second boundary line (52) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=90 degrees and the longitudinal engine pod coordinate X=L/4 and
• the end point (52b) of the second boundary line (52) is the point on the circumference of the engine pod with the circumferential engine pod angle phi=55 degrees and the longitudinal engine pod coordinate X=L·⅔, and
• wherein the boundary line respectively is the shortest line between its point of origin and its end point that extends on the outer circumference of the engine pod.