Aircraft Flap Vortex Generation Portion for Noise Reduction
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Solution Overview
Problem
Aircraft flaps generate noise due to wing tip vortices, and existing noise reduction technologies are either inefficient or increase weight and complexity.
Innovation Solution
A wing or flap design featuring a vortex generation portion on the upper surface near the tip, which creates a second vortex with the same rotation direction as the primary vortex, dispersing and redirecting the sound-producing vortices to reduce noise, using protruding members that form a predetermined angle to the airflow.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Object-affected harmful factors
If a flow suppression portion is provided on the upper surface side of the leading-edge of a tip end of a flap main body to separate the flow and reduce lift at the flap end, then noise from the tip vortex is reduced, but the aerodynamic performance (lift) is degraded
Solution Approach 1:
The invention generates a second vortex using a vortex generation portion (protruding member) that has the same rotation direction as the first vortex. This second vortex collides with and aggregates the first vortex, dispersing the vortex energy in a wider region and reducing noise. The key insight is to use vortex generation rather than suppression, converting the harmful concentrated vortex into a beneficial dispersed vortex pattern that reduces noise while preserving lift.
Solution Approach 2:
The invention changes the vortex characteristics by introducing a second vortex with the same rotation direction, altering the vortex aggregation pattern. This parameter change (adding a second vortex with specific rotation direction) transforms the flow structure to disperse the vortex energy, reducing noise without the need to suppress the primary vortex that generates lift.
2Object-affected harmful factors
If existing noise reduction technologies are applied to reduce wing tip vortex noise, then noise is reduced, but weight and device complexity increase
Solution Approach 1:
The invention applies a localized vortex generation portion (protruding member) at a specific location on the upper surface near the wing tip, rather than implementing a complex overall structural modification. This local intervention generates the second vortex that aggregates with the first vortex to reduce noise, achieving noise reduction with minimal added complexity and weight.
Solution Approach 2:
The invention achieves noise reduction by changing the vortex flow parameters through a simple protruding member geometry, rather than implementing complex active control systems or heavy structural modifications. The protruding member's shape and position are optimized to generate the second vortex with appropriate characteristics for noise reduction.
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 noise from wing tip vortices by dispersing and redirecting the vortices, minimizing sound pressure on the upper surface and weight, while maintaining aerodynamic performance.
Implementation Method 1
a vortex generation portion that is provided in a region adjacent to the wing tip on an upper surface of the wing-like member and generates, from a fluid flowing in a wing span direction of the wing-like member, a second vortex having the same direction of rotation as that of a first vortex generated at the wing tip
Implementation Method 2
the second vortex collides with the first vortex. Since the second vortex has the same direction of rotation as that of the first vortex, this makes the first vortex an aggregation of a plurality of vortexes, and those vortexes are dispersed in a region wider than the region of the first vortex
Data Source
Figure 1
Figure 2(a)~2(b)
Figure 3
AI summary
[Object] To reduce noise resulting from a wing tip vortex of a wing such as a flap. [Solving Means] A flap 3 of an aircraft includes a flap main body 8 provided to a parent wing 2 in a deployable manner, and a vortex generation portion 50 including a protruding member 5, the protruding member 5 being provided to protrude from an upper surface 301 at least at an end 40 of the flap main body 8 on an outboard side OTB in a span direction D2 and forming a predetermined angle to an axial direction D1 of the aircraft. A rear end 52 of the protruding member 5 is located on the side adjacent to a side-end edge 301A at the end 40 of the flap main body 8 in the span direction D2 relative to a virtual line VL passing through a front end 51 of the protruding member 5 and being parallel to the axial direction D1.