Abstract: Disclosed is a mast for the suspension of a bypass turbine engine beneath a wing of an aircraft in which the wing has at least one flap. The mast includes a rear fairing that protrudes rearward of a trailing edge of the wing and is mounted so as to tilt in a deployed downward position as the flap is deployed in a downward position. The rear fairing is positioned to enter a cold flow of the turbine engine, when deployed in the downward position. The rear fairing further supports at least one aerodynamic element that generates vortices that reduce, if not eliminates, vibrations to which the rear fairing is subjected.

Abstract: The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.

Abstract: The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.

Abstract: The flight of an aircraft is controlled by controlling the aircraft propulsion thrust and adjusting aerodynamic control elements so that the aircraft flies along a specified flight path. In order to reduce wake vortices generated by and trailing behind the aircraft, a wake vortex parameter is determined as a function of a spoiler deflection, and a spoiler element is adjusted to a spoiler deflection value in an optimum range in which the spoiler influence on the wake vortex parameter is maximized and the spoiler influence on the aircraft performance is at its lowest level for achieving that maximum spoiler influence on the wake vortex parameter.

Abstract: An apparatus for accelerating a destruction of a vortex is formed at the rear of a wing of an aircraft by a merging of first and second co-rotating eddies. A perturbation device is disposed adjacent of an area of creation of the first co-rotating eddy. The device is configured to generate a periodic perturbation having a wavelength capable of exciting at least on instability mode of the first eddy.

Abstract: A method of accelerating a destruction of a vortex formed at a rear of a wing of an aircraft by merging first and second co-rotating eddies. A periodic perturbation is generated adjacent an area of creation the first eddy. The periodic perturbation has a wavelength capable of exciting at least one instability mode of the first eddy.

Abstract: A device for accelerating the destruction of contra-rotating vortices formed at the rear of wings of a moving body by the merging of at least two co-rotating eddies includes, on each of the wings, at least one perturbator which is positioned in the vicinity of the area of creation of one of the co-rotating eddies associated with the wing. Each of the perturbators generates a periodic perturbation of the flow, which has a wavelength capable of exciting at least one of the instability modes of the corresponding eddy in such a way as to increase the core of the contra-rotating vortex which is created from this eddy, in such a way that the diameter of the core becomes greater than a predetermined proportion of the inter-vortex distance.

Abstract: The said device (1), for accelerating the destruction of contra-rotating vortices (5A, 5B) formed at the rear of wings (3A, 3B) of the moving body (2) by the merging of at least two co-rotating eddies (7A, 8A; 7B, 8B), comprises, on each of the wings (3A, 3B), at least one perturbation means (11) which is positioned in the vicinity of the area (10A, 10B) of creation of one (8A, 8B) of the said co-rotating eddies associated with the wing (3A, 3B). Each of the perturbation means (11) generates a periodic perturbation of the flow, which has a wavelength capable of exciting at least one of the said instability modes of the corresponding eddy (8A, 8B) in such a way as to increase the core of the contra-rotating vortex (5A, 5B) which is created from this eddy (8A, 8B), in such a way that the diameter (dA, dB) of the core becomes greater than a predetermined proportion of the inter-vortex distance (D).