Wing Tip Device Recess for Flow Interference Reduction
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Solution Overview
Problem
The addition of winglets to aircraft wings can create interference effects that increase drag and reduce lift, adversely affecting aircraft performance due to changes in the trailing edge trace and spanload.
Innovation Solution
Incorporating a recess on the surface of the wing tip device near the root, with convex and concave portions in the chordwise direction, to reduce flow interference effects at the junction of the wing and winglet, thereby minimizing drag and improving aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a winglet is added to the wing tip, then induced drag is reduced and aerodynamic performance is improved, but flow interference effects increase causing increased drag and reduced lift
Solution Approach 1:
The patent applies local quality by creating a recess with specific convex and concave portions at the junction area between the wing and winglet. This localized geometric modification changes the flow characteristics specifically at the interference zone without altering the overall winglet configuration, thereby reducing flow interference effects while maintaining the drag-reduction benefits of the winglet.
Solution Approach 2:
The recess incorporates curved surfaces with specific convex and concave portions rather than sharp angles or flat surfaces. These curved transitions smooth the flow passage at the junction, reducing flow separation and interference effects while maintaining structural integrity and aerodynamic efficiency.
2Productivity
If the winglet is fastened to the wing outboard portion, then the trailing edge trace and spanload are modified to reduce induced drag, but interference effects adversely affect aircraft performance
Solution Approach 1:
The recess is specifically located at the junction area where the winglet meets the wing outboard portion. This localized modification addresses the interference problem at the critical connection zone while preserving the overall spanload distribution and trailing edge trace geometry that provide the aerodynamic efficiency benefits.
Solution Approach 2:
The recess transforms the harmful flow interference and separation at the junction into a beneficial smooth flow pattern. By introducing the concave and convex portions, the design converts what would be a source of drag and lift reduction into an aerodynamic feature that maintains attached flow and reduces interference effects.
Applied Scientific Principles
This section explains which scientific principles are used to turn an abstract innovation direction into a practical engineering solution.
Function Achieved in This Case
The recessed design reduces flow separation and double-shock pressure fields, leading to decreased aircraft drag and enhanced high-speed buffet margin, improving overall aerodynamic efficiency.
Implementation Method 1
A surface of each wing tip device has a recess that reduces flow interference effects at a junction of the wing and the wing tip device
Implementation Method 2
The recessed design reduces flow separation and double-shock pressure fields
Data Source
AI summary
An aerodynamic lift structure includes a wing and at least one wing tip device at an outboard portion of the wing. A surface of each wing tip device has a recess that reduces flow impact at a junction of the wing and the wing tip device.