Leading-Edge Slat Gap Geometry for Low-Drag Wing Assemblies
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Solution Overview
Problem
Existing aircraft wing designs with fixed or movable leading-edge slats face challenges in accelerating airflow without significantly increasing drag, limiting cruising speed and requiring complex mechanisms for varying gap dimensions.
Innovation Solution
A wing arrangement with a leading edge slat extending beyond the main wing by at least 20% of the total length, featuring a larger airflow inlet and a constant outlet, utilizing the Bernoulli effect to accelerate airflow, and optionally incorporating a movable nose to adjust inlet size.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Speed
If a fixed leading-edge slat is used to accelerate airflow and increase lift at low speeds, then takeoff and landing speeds are reduced, but drag increases and cruising speed is limited
Solution Approach 1:
The leading-edge slat is designed to be movable rather than fixed, allowing it to change position between extended (for low-speed lift enhancement during takeoff and landing) and retracted (for reduced drag during cruise), thus adapting to different flight phases
Solution Approach 2:
The slat operates in periodic cycles: extended during takeoff and landing phases to increase lift, then retracted during cruise phase to minimize drag, creating alternating periods of high and low drag corresponding to different flight requirements
2Adaptability or versatility
If movable leading-edge slats are used to vary gap dimensions for different flight phases, then adaptability is improved, but device complexity increases
Solution Approach 1:
The slat is designed with simple movable capability that allows it to assume two primary positions (extended and retracted) corresponding to different flight phases, providing adaptability without requiring complex multi-position adjustment mechanisms
Solution Approach 2:
The gap dimensions between the slat and main wing are varied by changing the slat's position parameter, allowing the system to adapt to different flight conditions through a single geometric parameter change rather than complex mechanism 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
Enhances airflow acceleration on the main wing, reducing drag and allowing higher cruising speeds while maintaining lift at low speeds, with simplified mechanisms for takeoff and landing operations.
Implementation Method 1
the flow inlet be larger than the flow outlet, so that a Bernoulli effect occurs due to an airflow in the gap
Data Source
Figure 1
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Figure 5
AI summary
The invention relates to a wing assembly (10) in the form of a propeller of a fixed-wing aircraft or a gyroplane, or in the form of a rotor blade of a main and/or auxiliary rotor of an aircraft with wings, a helicopter, or a gyroplane, or in the form of a rotor blade of a wind turbine rotor. The wing assembly (10) comprises a main wing (12) and a leading edge slat (14) attached to it in front of the main wing (12) opposite to a flow direction (22), such that a gap (16) with a flow inlet (18) and a defined, fixed flow outlet (20) is formed between the leading edge slat (14) and the main wing (12).Viewed in a vertical cross-section along the flow direction (22), the length (D) of a section (32) of the leading edge slat (14) extending forward against the flow direction (22) beyond a length (A) of the main wing (12) is at least 20% of the total length (C) of the wing assembly (10) in the flow direction (22). It is proposed that the flow inlet (18) be larger than the flow outlet (20) so that an airflow (24) in the gap (16) creates a Bernoulli effect.