Wing tip device

Abstract

A wing tip device having a first wing tip device element for attaching at a first wing tip device element root to a tip of an aircraft wing, and a second wing tip device element extending from a second wing tip device element root to a second wing tip device element tip, the second wing tip device element root outboard, when viewed in the wing planform direction, of the first wing tip device element root; the first wing tip device element having a first wing tip device element leading edge and a first wing tip device element trailing edge, and the second wing tip device element having a second wing tip device element leading edge and a second wing tip device element trailing edge; and a fairing between the first and second wing tip device element which extends aft from the second wing tip device element trailing edge.

Description

RELATED APPLICATION[0001]This application claims priority to United Kingdom GB Application Number: GB 1815357.7 filed Sep. 20, 2018, the entirety of which is incorporated by reference.FIELD OF THE INVENTION[0002]The present invention relates to a wing tip device, a wing including the wing tip device, an aircraft including the wing, and a method of attaching a wing tip device.BACKGROUND OF THE INVENTION[0003]Interference effects between two objects in an airflow can be created when the wetted surfaces of those objects are in close proximity. For example, interference effects exist between an aircraft's fuselage and its wings. These effects can be particularly pronounced on wing tip devices with multiple lifting surfaces, such as split winglets, due to both surfaces generating lift and the sharp intersection of a downlet having horseshoe vortex interference effects.[0004]At the rearward junction of these lifting elements, adverse pressure gradients are present from the two lifting sur...

AI Technical Summary

Benefits of technology

The patent describes a fairing that is added to an aircraft to reduce drag and increase efficiency. By placing the fairing between the wing tip devices, it reduces interference and vortical flow, resulting in less drag at high speeds. The fairing also extends forward of the wing tip device, reducing the impact of a horseshoe vortex and associated increases in drag. Overall, the fairing improves the smoothness and streamlining of the aircraft, leading to better performance.

Problems solved by technology

For example, interference effects exist between an aircraft's fuselage and its wings.

These effects can be particularly pronounced on wing tip devices with multiple lifting surfaces, such as split winglets, due to both surfaces generating lift and the sharp intersection of a downlet having horseshoe vortex interference effects.

At the rearward junction of these lifting elements, adverse pressure gradients are present from the two lifting surfaces, the combination of which can cause excessive boundary layer growth and increased drag.

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