Multi-Winglet Airplane Wing Drag Reduction
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Solution Overview
Problem
Conventional wing designs for airplanes suffer from wingtip vortices, which reduce lifting efficiency, increase noise, and energy loss, and can be detrimental to following aircraft, highlighting the need for an improved winglet configuration that optimizes airflow and thrust.
Innovation Solution
The implementation of a wing design featuring at least two winglets on the outer wing end, where the upstream winglet is inclined relative to the downstream winglet by a dihedral angle between 37° to 80°, with specific angle intervals and orientations to broaden the airflow and produce a thrust component, decoupling the winglets for enhanced aerodynamic performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional single winglet design is used, then the structure is simple, but wing tip vortices reduce lifting efficiency and increase energy loss
Solution Approach 1:
The winglet is divided into multiple segments (first winglet and second winglet) arranged in a stepped configuration. Each segment has a specific spanwise length and is positioned at different heights, creating a multi-level structure that effectively disrupts and redirects wing tip vortices, thereby reducing energy loss compared to a conventional single winglet design.
Solution Approach 2:
The invention transitions from a conventional single-plane winglet to a three-dimensional stepped configuration. The first and second winglets are arranged at different vertical heights and spanwise positions, utilizing multiple spatial dimensions to control airflow and reduce vortices more effectively than a single-plane design.
2Force
If winglets are added to reduce wing tip vortices, then lifting efficiency improves, but drag increases due to additional surface area
Solution Approach 1:
The stepped winglet configuration applies different geometric properties to different local regions. The first winglet has a specific spanwise length and height, while the second winglet has different dimensions and positioning. This localized variation in geometry optimizes the balance between generating lifting force and minimizing drag across different sections of the wingtip structure.
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
This configuration reduces drag, enhances thrust contribution, and improves overall aerodynamic efficiency, allowing for a 2% reduction in overall drag and a small increase in lifting force, as demonstrated by computational fluid dynamics simulations.
Implementation Method 1
a pressure difference between a region above and a region below the wing, said pressure difference being the cause of the intended lift
Implementation Method 2
The basic function of a motorized airplane and its wings is to produce a certain velocity by means of a propulsion engine and to produce a required lift by means of wings of the airplane in the airflow resulting from the velocity
Implementation Method 3
Since there is some end of the wing, the airflow tends to compensate the pressure difference which results in a vortex. This wing tip vortex reduces the lifting effect of the wing, increases the noise produced, increases energy loss due to dissipation in the airflow
Implementation Method 4
This configuration reduces drag, enhances thrust contribution, and improves overall aerodynamic efficiency, allowing for a 2% reduction in overall drag
Data Source
AI summary
The invention relates to a wing with at least two winglets and a respective airplane. An upstream winglet broadens a region of inclined airflow and a more downstream winglet produces a thrust contribution therein.