Trailing Edge Contour Surfaces for Vortex Mixing and Drag Reduction
Find Innovative SolutionsGenerate Solutions
Solution Overview
Problem
Current methods for wake vortex control and drag alleviation do not effectively eliminate concentrated trailing wake vortices, leading to increased induced drag and aerodynamic noise, which limits aircraft separation distances and overall flight efficiency.
Innovation Solution
The integration of contour surfaces with riblets and compliant materials along the trailing edge of lifting or thrust-generating bodies, promoting vortex-mixing by varying the time and position of fluid stream mixing across the span, reduces the size and duration of wake vortices, thereby decreasing drag and noise.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional wake vortex control methods (wingtip devices, control surface oscillations) are used, then induced drag is reduced, but concentrated trailing wake vortices are not eliminated and aerodynamic noise remains high
Solution Approach 1:
The invention segments the trailing edge into multiple spanwise sections, each with independently controllable effectors that generate distributed vortex structures. This breaks up the single concentrated wake vortex into multiple smaller vortices distributed across the span, reducing the harmful concentration of kinetic energy while maintaining drag reduction benefits
Solution Approach 2:
The invention introduces spanwise vortex generators and trailing edge effectors as intermediary structures that actively manipulate the flow between the wing body and the wake. These intermediaries generate controlled vortex structures that promote mixing and dissipate the concentrated wake energy before it forms into harmful large-scale vortices
2Loss of time
If wake vortex mitigation is not implemented, then aircraft separation distances can be reduced, but concentrated wake vortices increase aerodynamic noise and reduce flight efficiency
Solution Approach 1:
The invention converts the harmful concentrated wake vortex kinetic energy into beneficial distributed mixing flows. By using spanwise vortex generators and trailing edge effectors, the kinetic energy that would otherwise form harmful concentrated vortices is redirected to create distributed vortex structures that enhance mixing and accelerate wake dissipation, allowing shorter separation distances without increasing noise
3Ease of manufacture
If traditional trailing edge designs are used, then manufacturing is simple, but vortex mixing is forced to occur only at wing tips reducing effectiveness
Solution Approach 1:
The trailing edge is segmented into multiple spanwise sections with distributed vortex generators and effectors. This segmentation allows vortex mixing to occur at multiple locations along the span rather than being forced only at the wing tips, significantly improving mixing efficiency while maintaining manufacturing simplicity through modular implementation
Solution Approach 2:
Different sections of the trailing edge are equipped with locally optimized vortex generators and effectors tailored to the specific flow conditions at each spanwise location. This local quality approach ensures optimal vortex mixing efficiency at each section while maintaining overall system simplicity and manufacturability
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 significantly reduces induced drag and vortex-induced noise, allowing for closer aircraft separation, increased flight efficiency, and reduced wear on control surfaces, while enhancing fuel efficiency and safety.
Implementation Method 1
promoting vortex-mixing by varying the time and position of fluid stream mixing across the span, reduces the size and duration of wake vortices
Data Source
AI summary
Disclosed are methods and apparatuses for mitigating the formation of concentrated wake vortex structures generated from lifting or thrust-generating bodies and maneuvering control surfaces wherein the use of contour surface geometries promotes vortex-mixing of high and low flow fluids. The methods and apparatuses can be combined with various drag reduction techniques, such as the use of riblets of various types and/or compliant surfaces (passive and active). Such combinations form unique structures for various fluid dynamic control applications to suppress transiently growing forms of boundary layer disturbances in a manner that significantly improves performance and has improved control dynamics.