Patent ID: 8523517

Claim:
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 (WP 1 ), and a subsequent second turning point (WP 2 ), 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 (WP 1 ) where the course of the local thickness (T) has a second gradient; a third zone from the first turning point (WP 1 ) to the second turning point (WP 2 ) 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 (WP 2 ) 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.