Retractable Wingtip Vortex Generators for Induced Drag Reduction
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Solution Overview
Problem
Modern commercial aircraft generate strong, long-lasting aerodynamic vortices at wing tips during take-off and landing, leading to increased resistance, noise, and interference with other aircraft, which hinders airport capacity and safety by increasing separation distances between aircraft.
Innovation Solution
A device with retractable and extendable aerofoil components is installed on the wing or regulating flap to decompose central tip vortices into a bundle of smaller vortices, reducing resistance and improving lift-to-drag ratio, allowing for closer aircraft spacing and enhanced flight control.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Force
If conventional wing tips are used (straight, rounded, or with winglets), then the aircraft generates necessary lift, but strong, long-lasting tip vortices are produced that increase resistance and interfere with other aircraft
Solution Approach 1:
The invention divides the single, strong tip vortex into multiple smaller vortices by introducing vortex generators at the wing tip. These generators create a bundle of weaker vortices that dissipate more quickly, reducing the harmful effects while preserving the necessary lift generation from the main wing.
Solution Approach 2:
The invention converts the harmful strong tip vortex into a beneficial pattern of multiple weaker vortices. The vortex generators deliberately create controlled turbulence that breaks down the coherent strong vortex structure, transforming a harmful phenomenon into a beneficial dissipation pattern that reduces drag and interference with following aircraft.
2Productivity
If strong tip vortices are generated to maintain lift at low speeds, then aircraft can operate during take-off and landing, but the separation distance between aircraft must be increased
Solution Approach 1:
By segmenting the tip vortex into multiple smaller vortices through vortex generators, the harmful effects are reduced sufficiently to allow shorter separation times between aircraft, thereby increasing airport throughput and productivity without compromising safety.
Solution Approach 2:
The invention changes the vortex parameters (strength, coherence, lifespan) by introducing vortex generators that modify the vortex structure. This parameter change allows reduced separation distances while maintaining adequate lift performance during critical low-speed operations.
3Force
If auxiliary lifting surfaces are extended to increase lift at high angles of attack, then take-off and landing performance improves, but stronger and longer-lasting vortices are produced
Solution Approach 1:
The vortex generators segment the strong, long-lasting vortices produced by extended lifting surfaces into multiple weaker, shorter-lived vortices. This segmentation reduces vortex lifespan and intensity while preserving the enhanced lift capability during take-off and landing operations.
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 solution effectively reduces the lifespan and circulation velocity of vortices, minimizing separation distances between aircraft, improving lift distribution, and reducing induced resistance while maintaining lift, thus enhancing airport efficiency and safety.
Implementation Method 1
Device for the generation of aerodynamic vortices... on the spanwise side edge of a main wing or wing or a regulating flap... at least one aerofoil component... decompose central tip vortices into a bundle of smaller vortices
Data Source
AI summary
A device for the generation of aerodynamic vortices to be arranged on the spanwise side edge of a wing, or a regulating flap adjustably arranged on the latter, which in each case have a chordwise direction and a spanwise direction, wherein the device is formed from one aerofoil component or from a plurality of aerofoil components, wherein the at least one aerofoil component is designed as a part that can be moved relative to the wing or regulating flap in its spanwise direction, wherein the device for vortex generation has an actuation device for the retraction and extension of the aerofoil components into a recess, and also a drive device to operate the actuation device. A regulating flap of a wing, and also a wing, with such a device for the generation of aerodynamic vortices, and a wing, which has at least two aerofoil segments at its side edge situated at the spanwise end.