Wing Geometry Modification for Propeller Wake Asymmetry
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Solution Overview
Problem
Current turbo-prop aircraft designs do not compensate for the propeller wake, leading to asymmetrical wing loading and increased trim drag, which results in fuel consumption and performance issues.
Innovation Solution
The wing geometry and propeller placement are modified to create localized areas of varying chord length and twist, aligning with the propeller wake to neutralize wing loading asymmetry, and the engine intake is adjusted to operate within the propeller wake, reducing trim drag and improving engine performance.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Power
If the propeller is installed on the aircraft, then the thrust generation is improved, but the propeller wake creates asymmetrical wing loading and increased trim drag
Solution Approach 1:
The patent applies local quality by modifying specific portions of the wing geometry (chord length and twist angle) at locations corresponding to the propeller wake influence zones. The wing is divided into multiple sections with different geometric characteristics to locally compensate for the asymmetrical loading caused by the propeller wake, rather than applying a uniform modification across the entire wing.
Solution Approach 2:
The patent implements preliminary anti-action by pre-configuring the wing geometry to counteract the expected asymmetrical loading from the propeller wake before flight. The chord length and twist angle are deliberately varied in advance to create opposing moments that balance the propeller-induced asymmetry, eliminating the need for trim adjustments during operation.
2Power
If the propeller wake flows over the wing, then thrust is generated, but localized areas of increased and decreased angle of attack create asymmetrical wing loading
Solution Approach 1:
The patent modifies the wing geometry with local variations in chord length and twist angle at specific stations along the span. These localized geometric changes are tailored to compensate for the asymmetrical angle of attack distribution caused by the propeller wake, creating a more uniform wing loading distribution across the wing span.
Solution Approach 2:
The patent deliberately introduces asymmetry into the wing geometry to counterbalance the asymmetry caused by the propeller. By varying the chord length and twist angle differently on each side of the wing, the design creates an asymmetrical configuration that produces symmetrical loading characteristics when operating with the propeller.
3Ease of manufacture
If current generation turbo-prop aircraft are designed as an assembly of components designed independently, then manufacturing is simplified, but the propeller and airframe do not compensate for each other's aerodynamic effects
Solution Approach 1:
The patent merges the propeller and airframe designs into an integrated system where the wing geometry is specifically tailored to work in conjunction with the propeller characteristics. The chord length and twist angle distributions are co-optimized to exploit the propeller wake effects, creating a unified aerodynamic system rather than treating the propeller and airframe as separate, independently designed components.
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 results in more symmetrical wing loading, reduced trim drag, decreased fuel consumption, and enhanced engine efficiency by exploiting the propeller slipstream effects.
Implementation Method 1
the propeller generating a helical or spiral air flow field, known as a propeller wake, which affects the downstream air flow field. The propeller wake includes axial and rotational components of velocity.
Implementation Method 2
The rotational components can either add or subtract to the lift generated by the wing, creating localized areas of increased or decreased lift along the wing span
Data Source
AI summary
An aircraft is disclosed, the aircraft having a fuselage having a centerline, and a wing extending from the fuselage and having a leading edge and a trailing edge. Additionally, the aircraft includes an engine mounted to the wing and having a rotating output shaft, and a propeller operably coupled to the output shaft and generating a rotating flow field to define a propeller wake when the propeller is rotated by the rotating output shaft. The propeller is located forward of the leading edge of the wing, so the propeller wake flows over the wing forming localized areas of effectively increased angle of attack generating a corresponding increased wing loading, with the wing having corresponding localized areas of reduced chord length to neutralize the otherwise increased wing loading. A method of countering the aerodynamic effects of propeller wake acting on a wing is also disclosed.