Serrated Wing Leading Element Trailing Edge for Flow Control
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Solution Overview
Problem
Conventional aircraft wing designs face challenges with flow separation over high-lift sections, particularly due to suboptimal slot geometries and the use of discrete vortex generators, which increase manufacturing complexity, cost, and drag, while also introducing space constraints and maintenance issues.
Innovation Solution
The design incorporates serrated or chevroned trailing edges on the leading element, which disrupt airflow and create vortices before it passes through the gap between the leading and trailing elements, effectively suppressing flow separation without the need for separate vortex generators.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If discrete vortex generators are used to prevent flow separation, then flow attachment is improved, but device complexity and manufacturing cost increase
Solution Approach 1:
The invention extracts the vortex generation function from separate discrete components and integrates it directly into the trailing edge geometry of the leading element. The serrated trailing edge itself generates the necessary vortices, eliminating the need for additional vortex generator devices.
Solution Approach 2:
The invention merges the trailing edge structure with the vortex generation function. The serrated trailing edge of the leading element serves dual purposes: maintaining aerodynamic continuity and generating vortices to prevent flow separation on the flap, combining structural and flow control functions into one element.
2Reliability
If discrete vortex generators are installed on the wing, then flow separation is reduced, but manufacturing cost and complexity increase
Solution Approach 1:
The invention extracts the vortex generation function from separate manufactured components and embeds it directly into the trailing edge geometry of the leading element, which is manufactured as a single integrated piece with the wing structure.
Solution Approach 2:
The trailing edge structure is merged with the vortex generation function through serrations, eliminating the need for separate vortex generator manufacturing and installation processes, thereby reducing overall manufacturing cost and complexity.
3Force
If discrete vortex generators are added to the wing, then lift is enhanced by preventing flow separation, but drag increases
Solution Approach 1:
The invention extracts vortex generation from separate drag-producing components and integrates it into the existing trailing edge structure, where the serrations generate vortices with minimal additional drag penalty.
Solution Approach 2:
The trailing edge structure combines lift-enhancing vortex generation with minimal drag penalty, as the serrations are formed as part of the existing airfoil geometry rather than adding protruding elements that would increase pressure and friction drag.
4Reliability
If discrete vortex generators are used, then flow separation is suppressed, but maintenance requirements and space constraints increase
Solution Approach 1:
The invention extracts the vortex generation function from removable discrete components and integrates it into the fixed trailing edge structure, eliminating maintenance requirements associated with separate vortex generator devices.
Solution Approach 2:
The trailing edge structure merges vortex generation capability with the permanent wing structure, eliminating the need for separate maintenance of vortex generators while maintaining continuous flow control functionality.
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 approach reduces flow separation, enhances lift, and minimizes drag and maintenance concerns, while improving airflow mixing to reduce noise, thereby optimizing wing performance and efficiency.
Implementation Method 1
a trailing edge of the leading element proximate to the trailing element is configured to disrupt air flow as it flows over said trailing edge and through the gap
Implementation Method 2
This increases circulation around the wing element 2 and the slot 9 is designed so that that pressure distribution around the flap 3, in particular, the peak pressure at the leading edge, is suppressed to prevent flow separation on the flap upper surface
Data Source
AI summary
An aircraft wing comprising a leading element and a trailing element moveably coupled together, said elements being positionable relative to each other so that air can flow from the underside of the leading element over the top of the trailing element through a gap between the leading element and the trailing element, wherein a trailing edge of the leading element proximate to the trailing element is configured to disrupt air flow as it flows over said trailing edge and through the gap.