An engine nacelle for an aircraft, which engine nacelle comprises a nacelle housing with a first side and a second side and several fin-shaped vortex generators (21, 22, 23; 31, 32) and has a longitudinal axis which is the rotational axis of an engine to be mounted within the nacelle housing, wherein an engine-nacelle circumferential angle phi is defined with regard to the longitudinal axis and starts from a vertical axis of the nacelle housing intersecting the longitudinal axis and a middle axis of a pylon which runs along the longitudinal axis and at which the nacelle housing is adapted to be mounted, wherein at least two fin-shaped vortex generators (21, 22, 23; 31, 32) are arranged on at least one of the two sides (S1, S2) of the nacelle housing, characterised in that the frontmost point of a first vortex generator, which is positioned closest to the front of the nacelle, is placed at a position with an engine-nacelle longitudinal coordinate X >= L/4, wherein L is the length of the nacelle housing, X is the position on a longitudinal coordinate extending along the longitudinal axis of the nacelle housing and wherein the starting point of the engine-nacelle longitudinal coordinate is the point in which the entry plane of the nacelle housing intersects the longitudinal axis, and the frontmost point of the first vortex generator is located within a positioning corridor situated between two boundary lines (51, 52), wherein: ▪ the starting point (51 a) of the first boundary line is the circumferential point of the nacelle housing 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 is the circumferential point of the nacelle housing with the engine-nacelle circumferential angle phi = 25 degrees anc the engine-nacelle longitudinal coordinate X = L•2/3; ▪ the starting point of the second boundary line is the circumferential point of the nacelle housing with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4; ▪ the end point of the second boundary line is the circumferential point of the nacelle housing with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L•2/3; wherein in each case the boundary line is the line that extends over the external circumference of the nacelle housing and is the shortest line between the starting point on said external circumference and the end point on said external circumference. ▪ the starting point (51 a) of the first boundary line is the circumferential point of the nacelle housing 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 is the circumferential point of the nacelle housing with the engine-nacelle circumferential angle phi = 25 degrees anc the engine-nacelle longitudinal coordinate X = L•2/3; ▪ the starting point of the second boundary line is the circumferential point of the nacelle housing with the engine-nacelle circumferential angle phi = 90 degrees and the engine-nacelle longitudinal coordinate X = L/4; ▪ the end point of the second boundary line is the circumferential point of the nacelle housing with the engine-nacelle circumferential angle phi = 55 degrees and the engine-nacelle longitudinal coordinate X = L•2/3;