Wing Tip Guide Vane Assembly for Induced Drag Reduction
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Solution Overview
Problem
Conventional aircraft designs with winglets or split winglets are limited in their ability to reduce induced drag, as they do not effectively de-swirl airflow at the wingtips, leading to increased turbulence and reduced propulsive thrust.
Innovation Solution
The incorporation of a wing tip assembly with multiple stationary guide vanes, spaced and angled to de-swirl airflow, reduces induced drag by aligning the vanes with the aircraft's longitudinal direction and circumferential direction, with varying lengths and spacings to enhance airflow management.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If a winglet or split winglet is positioned at the outer end of the wing, then induced drag is reduced by de-swirling airflow, but the de-swirling capability is limited and turbulence remains
Solution Approach 1:
The wing tip assembly is segmented into multiple stationary guide vanes (at least three) spaced along the circumferential direction, each capable of independently de-swirling airflow in different sectors. This segmentation allows more comprehensive coverage of the swirling airflow compared to a single winglet structure, thereby reducing induced drag more effectively while maintaining manageable structural complexity through modular design
Solution Approach 2:
The invention transitions from the traditional two-dimensional winglet configuration to a three-dimensional wing tip assembly with guide vanes arranged circumferentially around the wing tip axis. This dimensional expansion allows the guide vanes to intercept and de-swirl airflow from multiple angular positions simultaneously, significantly enhancing the de-swirling capability and reducing induced drag beyond what conventional winglets can achieve
2Loss of energy
If multiple stationary guide vanes are spaced along the circumferential direction, then de-swirling capability is enhanced and induced drag is reduced, but the structural complexity increases
Solution Approach 1:
Each stationary guide vane is designed with specific local characteristics including varying lengths and optimized angular spacings along the circumferential direction. The guide vanes can have different span lengths and airfoil sections tailored to local flow conditions at different circumferential positions, allowing each element to optimally address the swirling flow in its specific sector while contributing to overall induced drag reduction
Solution Approach 2:
The invention utilizes parameter variations in the guide vane configuration, including the number of vanes (at least three), their circumferential spacing angles, and span lengths, to optimize de-swirling performance. By adjusting these parameters, the assembly can be tuned to match specific aircraft operating conditions and wing geometries, achieving effective induced drag reduction without excessive structural complexity
3Power
If guide vanes are positioned to de-swirl airflow, then propulsive thrust is enhanced, but manufacturing and installation complexity increases
Solution Approach 1:
The stationary guide vanes are pre-configured during manufacturing with predetermined circumferential spacing and orientations that are optimized for de-swirling airflow under typical operating conditions. This preliminary configuration allows the assembly to be manufactured as a integrated unit or pre-assembled modules, simplifying installation on the aircraft while ensuring optimal thrust enhancement performance from the outset without requiring complex field adjustments
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 wing tip assembly effectively de-swirls airflow, reducing induced drag and improving overall aircraft efficiency by minimizing wingtip vortices and enhancing propulsive thrust.
Implementation Method 1
Positioning a winglet, or alternatively a split winglet, at an outer end of each of the wings of the aircraft can reduce an induced drag on the aircraft by reducing the kinetic energy of the airflow that is lost to swirl over the outer end of the wing (i.e., 'de-swirling' such airflow)
Implementation Method 2
The wing tip assembly effectively de-swirls airflow, reducing induced drag and improving overall aircraft efficiency by minimizing wingtip vortices
Data Source
AI summary
An aircraft defines a longitudinal direction, a vertical direction, and a transverse direction. The aircraft includes a fuselage; and a wing extending from the fuselage generally along the transverse direction and defining an outer end along the transverse direction. The wing includes a wing tip assembly at the outer end of the wing, the wing tip assembly defining an axis substantially parallel to the longitudinal direction of the aircraft and a circumferential direction extending about the axis, the wing tip assembly including at least three stationary guide vanes spaced along the circumferential direction from one another.