Wingtip Shield Strut Layout for Induced Drag Reduction
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Solution Overview
Problem
Conventional wing designs suffer from significant lift-induced drag due to trailing vortices formed at the wingtips, which increase energy consumption and cause turbulence, and existing solutions like winglets only slightly improve the lift-to-drag ratio.
Innovation Solution
Implementing a wingtip shield that redirects airflow from the high-pressure side to the rear, reducing the formation of trailing vortices and generating a net thrust force, optionally with struts for structural integrity and improved aerodynamics.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Loss of energy
If conventional wing designs are used, then the basic wing structure is simple, but significant lift-induced drag is generated due to trailing vortices at the wingtips
Solution Approach 1:
The wingtip shield divides the wingtip region into separate high-pressure and low-pressure zones, preventing the mixing of air masses that creates trailing vortices. This segmentation of the flow field reduces induced drag without requiring a complete redesign of the entire wing structure.
Solution Approach 2:
The wingtip shield acts as an intermediary structure between the high-pressure lower surface and low-pressure upper surface of the wing. It redirects the airflow from the high-pressure region toward the rear instead of allowing it to wrap around the wingtip and form vortices, thereby reducing drag.
2Loss of energy
If winglets are added to the wingtips, then the lift-to-drag ratio is slightly improved, but the basic mode of operation of the wing remains unchanged and induced drag is not significantly reduced
Solution Approach 1:
Instead of extending the wing upward like conventional winglets, this invention places a shield on the lower surface of the wingtip that faces backward. This inverted approach redirects airflow in the opposite direction (toward the rear) rather than allowing it to wrap around the tip, fundamentally changing the flow pattern to reduce induced drag more effectively.
Solution Approach 2:
The wingtip shield changes the flow direction parameter by redirecting high-pressure air toward the rear instead of allowing it to circulate around the wingtip. This parameter change in airflow direction fundamentally alters the vortex formation mechanism and reduces induced drag more significantly than winglets.
3Loss of energy
If the wingspan is extended to reduce induced drag, then the lift-to-drag ratio improves, but the structural weight and complexity increase significantly
Solution Approach 1:
Instead of extending the entire wingspan to reduce induced drag, this invention applies a localized wingtip shield only at the critical wingtip region where vortices form. This local intervention addresses the root cause of induced drag without requiring increased wingspan and the associated weight penalty.
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
Significantly reduces induced drag by up to 53% and enhances the lift-to-drag ratio, improving flight efficiency and reducing energy consumption.
Implementation Method 1
a high pressure builds up on the bottom surface of the airplane wings, as the velocity of the air is converted into pressure... The pressure generated by the air velocity can be expressed as where Q is the dynamic pressure
Implementation Method 2
the air near the wingtip is naturally coerced to flow from the bottom to the top thereby creating a vortex flow, commonly called the 'trailing vortices'
Implementation Method 3
one or more struts may be added in the space between the wing and the wingtip shield. The struts add structural integrity and prevent or at least reduce vibration and flutter of the wing
Implementation Method 4
cross-section of the strut is shaped as an airfoil wing to reduce aerodynamic drag
Data Source
AI summary
Wingtip shields are described. In one embodiment, a wingtip shield includes an inner surface facing a high-pressure side of an airfoil. The airfoil is attached to the main body. The wingtip shield also includes an outer surface configured opposite from the inner surface. The wingtip shield also includes a wingtip shield strut connecting the inner surface with the airfoil. In some embodiments, the wingtip shield includes multiple wingtip shield struts that are arranged parallel to each other. In some embodiments, spacings between wingtip shield struts are same. In some embodiments, a cross-section of the strut has a shape of a National Advisory Committee for Aeronautics (NACA) airfoil.