Bionic Airfoil Undulations for Low-Reynolds Lift Stability
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Solution Overview
Problem
Conventional airfoil designs struggle to achieve high aerodynamic performance in low Reynolds number regimes, such as those encountered in low density or small velocity conditions, particularly in environments like the Martian atmosphere.
Innovation Solution
A method for generating airfoil manufacturing data by marking support points on a template airfoil, constructing connecting line segments without intersections, and forming undulating surfaces inspired by dragonfly wings to create a bionic airfoil design, which includes protruding and recessed undulations for vortex flow enhancement.
Engineering Contradictions & Design Principles
Engineering Contradiction Analysis
1Reliability
If conventional airfoil designs are used, then manufacturing simplicity is maintained, but aerodynamic performance in low Reynolds number regimes deteriorates
Solution Approach 1:
The airfoil surface is segmented into multiple planform sections along the spanwise direction, with each section having a different camber value. This segmentation allows the airfoil to incorporate complex bionic features while maintaining manufacturing feasibility through modular construction approaches.
Solution Approach 2:
Different regions of the airfoil surface are assigned different geometric properties, specifically varying camber values across the span. The camber distribution is optimized locally to mimic dragonfly wing characteristics, with higher camber values in regions that benefit from enhanced lift generation and lower camber values where structural simplicity is prioritized.
2Reliability
If bionic surface features are added to improve low Reynolds number performance, then aerodynamic efficiency increases, but manufacturing complexity increases
Solution Approach 1:
The airfoil incorporates an adaptable mechanism that allows dynamic adjustment of the camber distribution along the span. This dynamic capability enables the airfoil to optimize its aerodynamic performance for different flight conditions while maintaining a relatively simple base structure that is easier to manufacture.
Solution Approach 2:
The invention changes the geometric parameters of the airfoil, specifically the camber values, to create bionic surface features. By systematically varying the camber parameter across different spanwise locations, the design achieves enhanced aerodynamic performance while the parameter-based approach facilitates systematic manufacturing processes.
3Reliability
If support points are marked and connecting line segments are constructed to form undulating surfaces, then vortex flow enhancement is achieved, but the complexity of the generation process increases
Solution Approach 1:
The method performs preliminary actions by first marking support points on the template airfoil surface and pre-defining the camber values for each section before constructing the final three-dimensional model. This preliminary organization of geometric data simplifies the subsequent manufacturing and modeling processes despite the increased complexity of the final bionic surface.
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
The derived airfoils exhibit improved aerodynamic performance and mechanical stability, reducing the risk of stalling and enhancing lift-to-drag ratios, particularly in low Reynolds number conditions.
Implementation Method 1
forming undulating surfaces inspired by dragonfly wings to create a bionic airfoil design, which includes protruding and recessed undulations for vortex flow enhancement
Data Source
Figure 1A~1D
Figure 1E~1F
Figure 2A~2B
AI summary
In order to generate a bionic derived airfoil (50) from a conventional template airfoil (10), the invention proposes marking a plurality of upper support points (22) and lower support points (24) that are arranged on an upper template surface (12) and on the lower template surface (14) of the template airfoil (10), respectively. A plurality of connecting line segments (44, 84) is constructed between the upper support points (22) and the lower support points (24) in a manner that none of the connecting line segments (44, 84) intersect with each other. The resulting zig-zag pattern can be used as an aerodynamic surface of the bionic derived airfoil (50) or as a basis for a construction line (54) from which the bionic derived airfoil (50) is further generated. The resulting airfoil manufacturing data are given to an appropriate manufacturing facility for manufacture of the bionic derived airfoil (50).