| 摘要 |
The invention relates to a wingtip extension (10) with a leading edge (14) and a trailing edge (16) which may be applied to an outer end (8) of a wing (2), wherein the leading edge (14) is at least partly essentially straight and the straight section has a leading edge sweep angle which is larger than the leading edge sweep angle of the wing (2) and the local depth of the wingtip extension (10) continuously reduces from a connector region for connecting to the wing and the outer end of the wingtip extension (10). A vortex collapse region can be placed directly behind the wing tip by means of said wingtip extension in delta wings the wing edge vortex collapsing at the core thereof and then becomes unstable such that the vortex drag of the aircraft can be reduced. The invention further relates to a wing (4) provided with such a wingtip extension and an aircraft provided with such a wing. |
