Cross-sectional profile for the struts or the fairing of struts and service lines of a turbofan engine

An aerodynamically shaped, symmetrical cross-sectional profile for at least one chosen from a strut, a fairing of a strut and a service line positioned in at least one chosen from a bypass duct and a core-flow duct of a turbofan engine,

• wherein the profile is defined by a course of a local thickness (T) and a position (PMT) of maximum thickness (MT) on both sides over a central chord (C) extending from a leading edge (LE) to a trailing edge (TE) of the at least one chosen from the strut, the fairing of a strut and the service line,
• wherein, in order to avoid flow separations, the course of the local thickness (T) between the position of maximum thickness (PMT) and a certain trailing-edge position (PTE) has a first turning point (WP1), and a subsequent second turning point (WP2), with the trailing-edge position (PTE) being positioned at approximately 95% of a length of the chord (C) and having a trailing-edge thickness (TET);
• the profile including:
• a first zone from the leading edge (LE) to the position of maximum thickness (PMT);
• a second zone from the position of maximum thickness (PMT) to the first turning point (WP1) where the course of the local thickness (T) has a second gradient;
• a third zone from the first turning point (WP1) to the second turning point (WP2) where the course of the local thickness (T) has a third gradient differing from the second gradient;
• and
• a fourth zone from the second turning point (WP2) to the trailing-edge position (PTE) where the course of the local thickness (T) has an increasingly negative gradient as compared to the third gradient.