Aircraft wing imitating seathead whale fin limb molded line and aircraft
By imitating the wing design of the humpback whale flipper line, the problem of flow separation in traditional wings at a large angle of attack is solved, a higher lift-to-drag ratio and better aerodynamic performance are achieved, which is suitable for the aircraft climbing phase.
Patent Information
- Application Number
- CN202511012019.2
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-07-22
- Publication Date
- 2025-10-10
AI Technical Summary
Traditional wings suffer from severe flow separation within a wide angle of attack range, resulting in a decreased lift-to-drag ratio and severe performance loss, especially during the aircraft's climb phase.
The wing design imitates the lines of the humpback whale's flippers, including a continuously undulating mid-arc line and a structure with maximum curvature near the trailing edge. The wing line style is optimized by combining the biological characteristics of the humpback whale's flippers.
It significantly improves the lift-to-drag ratio within the 9° to 15° angle of attack range, suppresses flow separation, reduces drag, saves fuel consumption, and improves aircraft operating efficiency and load-bearing capacity.
Smart Images
Figure CN120756647A_ABST
Abstract
Description
Technical Field
[0001] The invention relates to the technical field of aircraft wings, and in particular to an aircraft wing imitating the profile of a humpback whale flipper and an aircraft. Background Art
[0002] As a key component of an aircraft, the aerodynamic performance of the wing directly impacts its flight efficiency, fuel economy, and safety. Therefore, the selection and design of the wing is crucial. Traditional wing designs typically utilize standard airfoils (such as the NACA series), which offer excellent aerodynamic performance at low angles of attack. However, at higher angles of attack, flow separation easily occurs on the wing surface, resulting in slow lift growth, a decrease in lift-to-drag ratio, and significant performance loss. This drawback is particularly pronounced during the aircraft's climb phase.
[0003] In recent years, the application of bionics in the aviation field has gradually attracted attention. Although biological characteristics have been applied to aircraft, existing designs lack the precise extraction and application of the biological shapes of bionic organisms, which often leads to certain limitations when converting them into actual wing structures. Summary of the Invention
[0004] The purpose of the present invention is to address the problems existing in the prior art and provide an aircraft wing and an aircraft that imitate the profile of a humpback whale flipper, which can effectively suppress flow separation on the wing surface within a certain range of attack angles and significantly improve the aerodynamic performance of the aircraft.
[0005] To achieve the above object, the technical solution adopted by the present invention is: An aircraft wing imitating the profile of a humpback whale's flipper comprises a wing body. The profile of the cross-sectional structure of the wing body imitates the profile of a humpback whale's flipper, comprising an airfoil leading edge, an airfoil upper camber line, an airfoil lower camber line, and an airfoil trailing edge connected in a closed loop. A continuously undulating airfoil mid-camber line is present between the airfoil leading edge and the airfoil trailing edge. The maximum thickness of the wing body is located in the front half of the cross-sectional structure, and the maximum camber of the wing body is located in the rear half of the cross-sectional structure and close to the airfoil trailing edge.
[0006] The aircraft wing imitating the humpback whale flipper line has a greater lift-to-drag ratio within a certain angle of attack range by improving the line style of the wing body, significantly improving the aerodynamic performance of the wing within this angle of attack range, enabling the aircraft to quickly obtain the required lift capability during the climb phase, reducing the resistance encountered, and saving fuel consumption.
[0007] This invention applies biomimetic concepts to aircraft, providing new insights into their design and optimization. By precisely extracting and applying the cross-sectional shape of a humpback whale's flipper, the present invention fully considers its limitations and characteristics when translating its characteristics into a practical wing structure. The result is an aircraft wing designed to mimic the profile of a humpback whale's flipper. This wing structure not only perfectly inherits the excellent properties of the flipper's profile in suppressing flow separation and delaying stall, but also offers improved flight suitability and is well-suited for aircraft use.
[0008] Furthermore, the camber line of the airfoil shows a trend of first rising, then falling, and then rising again from the leading edge of the airfoil to the trailing edge of the airfoil, and the amplitude of the first rising, then falling, and then rising increases successively.
[0009] Furthermore, the airfoil mid-camber line continuously fluctuates relative to the airfoil chord line of the wing body, and the maximum fluctuating height of the airfoil mid-camber line relative to the airfoil chord line is the maximum camber position of the wing body.
[0010] Furthermore, the distance between the maximum camber of the wing body and the trailing edge of the airfoil does not exceed 1 / 5 of the length of the airfoil chord of the wing body.
[0011] Furthermore, the airfoil leading edge is the first 15% of the airfoil chord length of the wing body, and the airfoil trailing edge is the last 15% of the airfoil chord length of the wing body.
[0012] Furthermore, the sizes and shapes of the airfoil leading edge, the airfoil upper camber line, the airfoil lower camber line, and the airfoil trailing edge satisfy the following relationship: r=4%C; t=19.95%C; X t =25.86%C; f=2.09%C; X f =86.88%C; Where r is the radius of the leading edge of the airfoil; t is the maximum thickness of the wing body; X t is the horizontal coordinate value corresponding to the maximum thickness position of the wing body; f is the maximum curvature of the wing body; X f is the horizontal coordinate value corresponding to the maximum curvature of the wing body; C is the length of the airfoil chord of the wing body.
[0013] Furthermore, the shape of the cross-sectional structure is defined by given coordinate points. Assuming that the origin of the coordinates is located at the front end of the airfoil chord of the wing body, when the length of the airfoil chord is defined as C=1, the coordinate values corresponding to the upper and lower surfaces of the wing body are: , Among them, X represents the horizontal coordinate and Y represents the vertical coordinate.
[0014] Furthermore, the camber line of the airfoil is distributed in a non-monotonic undulating manner along the length direction of the airfoil chord line, and three extreme camber points are formed at 6.07%C, 38.23%C and 86.88%C of the airfoil chord line, respectively. The three extreme camber points are 0.38%C, 0.94%C and 2.09%C, respectively. Among them, the 2.09%C position is the position where the maximum camber of the wing body is located.
[0015] Furthermore, the longitudinal length of the wing body is more than twice, preferably about three times, the length of the airfoil chord line. That is, the span width of the wing body is about three times the length of the airfoil chord line.
[0016] An aircraft having the above-mentioned aircraft wings imitating the humpback whale flipper profile.
[0017] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. The aircraft wing imitating the humpback whale flipper line has a greater lift-to-drag ratio within the range of 9° to 15° angle of attack by improving the line style of the wing body, which significantly improves the aerodynamic performance of the wing within this angle of attack range, so that the aircraft can quickly obtain the required lift capability during the climb phase, reduce the resistance encountered, and save fuel consumption; 2. The aircraft wing imitating the humpback whale flipper line can effectively suppress flow separation on the wing surface within a certain range of angle of attack, significantly improving the aerodynamic performance of the aircraft; 3. Through the improvement, the aircraft wing imitating the humpback whale flipper line can carry more weight than the existing aircraft wing at the same angle of attack, thereby improving the aircraft's working efficiency. ; 4. Compared with the existing airfoils, the maximum thickness of the wing of this aircraft is smaller, and the relative position of the maximum thickness is closer to the leading edge of the airfoil. The arc line of the airfoil is non-monotonic and undulating along the chord direction, forming multiple extreme curvature points, which is more in line with the structural characteristics of the flippers of creatures such as humpback whales, so that the fluid can better adhere to the surface of the airfoil; 5. The present invention accurately extracts and applies the cross-sectional shape of the humpback whale flippers. When converting the characteristics of the humpback whale flippers into actual wing structures, it fully considers their limitations and characteristics, and designs the aircraft wing of the present invention that imitates the humpback whale flipper line. This wing structure not only perfectly inherits the excellent characteristics of the flipper line in suppressing flow separation and delaying stall, but is also more suitable for flight and can be well used on aircraft. BRIEF DESCRIPTION OF THE DRAWINGS
[0018] Figure 1 This is a schematic cross-sectional view of an aircraft wing imitating the fin profile of a humpback whale according to the present invention; Figure 2 This is an overall schematic diagram of an aircraft wing imitating the profile of a humpback whale flipper according to the present invention; Figure 3 A comparison chart of the lift-to-drag ratio between the bionic wing provided by an embodiment of the present invention and the NACA634-021 wing; Figure 4 Comparison diagrams of the equivalent surfaces of a NACA634-021 wing and a bionic wing provided by an embodiment of the present invention at angles of attack of 9°, 12°, and 15° are shown (left: NACA634-021 wing; right: bionic wing); In the figure: 1. Leading edge of airfoil; 2. Upper camber line of airfoil; 3. Chord line of airfoil; 4. Middle camber line of airfoil; 5. Lower camber line of airfoil; 6. Trailing edge of airfoil; 7. Wing body. DETAILED DESCRIPTION
[0019] The following will clearly and completely describe the technical solution of the present invention in conjunction with the accompanying drawings. Obviously, the embodiments described are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.
[0020] In the description of the present invention, it should be noted that the terms "middle", "upper", "lower", "left", "right", "inside", "outside", etc., indicating directions or positional relationships, are based on the directions or positional relationships shown in the accompanying drawings. They are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction. Therefore, they cannot be understood as limiting the present invention.
[0021] like Figure 1 and Figure 2 As shown, an aircraft wing imitating the profile of a humpback whale's flipper includes a wing body 7. The profile of the cross-sectional structure of the wing body 7 imitates the profile of a humpback whale's flipper, including an airfoil leading edge 1, an airfoil upper camber line 2, an airfoil lower camber line 5, and an airfoil trailing edge 6 connected in a closed loop. A continuously undulating airfoil mid-camber line 4 is present between the airfoil leading edge 1 and the airfoil trailing edge 6. The maximum thickness of the wing body 7 is located in the front half of the cross-sectional structure, and the maximum curvature of the wing body 7 is located in the rear section of the cross-sectional structure and close to the airfoil trailing edge.
[0022] The aircraft wing imitating the humpback whale flipper line has a greater lift-to-drag ratio within a certain angle of attack range by improving the line style of the wing body, significantly improving the aerodynamic performance of the wing within this angle of attack range, enabling the aircraft to quickly obtain the required lift capability during the climb phase, reducing the resistance encountered, and saving fuel consumption.
[0023] The aircraft wing imitating the humpback whale flipper line can effectively suppress flow separation on the wing surface within a certain range of attack angles, thereby significantly improving the aircraft's aerodynamic performance.
[0024] Through the improvement, the aircraft wing imitating the humpback whale flipper line can carry more weight at the same attack angle compared with the existing aircraft wing, thereby improving the working efficiency of the aircraft.
[0025] The present invention applies the concept of biomimetic to aircraft, providing a new approach for the design and optimization of aircraft. In nature, although humpback whales are large in size, they are able to turn flexibly during predation. Studies have found that the flippers with unique structures on both sides of their bodies play a key role. The wavy protrusions on the leading edge of their flippers have been proven to suppress flow separation and delay the occurrence of stall. The present invention accurately extracts and applies the cross-sectional shape of the humpback whale flippers. When converting the characteristics of the humpback whale flippers into actual wing structures, the limitations and characteristics of the flippers are fully considered, and the aircraft wing of the present invention that imitates the humpback whale flipper profile is designed. This wing structure not only perfectly inherits the excellent characteristics of the flipper profile in suppressing flow separation and delaying stall, but is also more suitable for flying and can be well used on aircraft.
[0026] The wing of this aircraft has obvious differences from existing wings in terms of its profile structure. The middle camber line 4 of the airfoil is a continuous undulating structure, which causes the shapes of the upper camber line 2 and the lower camber line 5 of the airfoil to change significantly. The maximum curvature of the wing body 7 is no longer close to the middle area of the wing, but close to the tail end. The maximum thickness of the wing body 9 is basically at the 1 / 4 position of the wing. Through these improvements, it has better performance in reducing drag and improving stability.
[0027] Furthermore, the airfoil center camber line 4 shows a trend of first rising, then falling, and then rising again from the airfoil leading edge 1 to the airfoil trailing edge 6, and the amplitude of first rising, then falling, and then rising increases successively. Such a setting makes its maximum curvature close to the tail section of the entire wing cross-sectional structure, and makes the end of the wing body have a downward pressure trend, which is beneficial to improving the aerodynamic performance of the tail section.
[0028] Furthermore, the airfoil camber line 4 continuously fluctuates relative to the airfoil chord line 3 of the wing body, and the maximum fluctuating height of the airfoil camber line relative to the airfoil chord line is the maximum camber position of the wing body.
[0029] Furthermore, the distance between the maximum curvature of the wing body 7 and the airfoil trailing edge 6 does not exceed 1 / 5 of the length of the airfoil chord line 3 of the wing body.
[0030] Furthermore, the airfoil leading edge is the first 15% of the airfoil chord length of the wing body, and the airfoil trailing edge is the last 15% of the airfoil chord length of the wing body.
[0031] Furthermore, the sizes and shapes of the airfoil leading edge 1, the airfoil upper camber line 2, the airfoil lower camber line 5, and the airfoil trailing edge 6 satisfy the following relationship: r=4%C; t=19.95%C; X t =25.86%C; f=2.09%C; X f =86.88%C; Where r is the radius of the leading edge of the airfoil; t is the maximum thickness of the wing body; X t is the horizontal coordinate value corresponding to the maximum thickness position of the wing body; f is the maximum curvature of the wing body; X f is the horizontal coordinate value corresponding to the maximum curvature of the wing body; C is the length of the airfoil chord of the wing body.
[0032] Furthermore, the shape of the cross-sectional structure is defined by given coordinate points. Assuming that the origin of the coordinates is located at the front end of the airfoil chord of the wing body, when the length of the airfoil chord is defined as C=1, the coordinate values corresponding to the upper and lower surfaces of the wing body are: , Among them, X represents the horizontal coordinate and Y represents the vertical coordinate.
[0033] In this embodiment, the Reynolds number of the aircraft wing is 1.8×10 5 The chord length of the airfoil is about 102mm and the wingspan width is about 306mm.
[0034] The camber line of the airfoil is distributed in a non-monotonic undulating manner along the length direction of the airfoil chord line, and three extreme camber points are formed at 6.07%C, 38.23%C and 86.88%C of the airfoil chord line, respectively. The three extreme camber points are 0.38%C, 0.94%C and 2.09%C, respectively. Among them, the 2.09%C position is the position where the maximum camber of the wing body is located.
[0035] Compared with existing airfoils, the maximum thickness of the wing of this aircraft is smaller and the relative position of the maximum thickness is closer to the leading edge of the airfoil. The arc line of the airfoil is distributed non-monotonously in the chord direction, forming multiple extreme curvature points, which is more in line with the structural characteristics of the flippers of creatures such as humpback whales, allowing fluid to better adhere to the airfoil surface.
[0036] The specific implementation scheme provided above was numerically simulated and compared with the aerodynamic characteristics of the NACA634-021 airfoil (hereinafter referred to as the basic airfoil) to demonstrate the feasibility of the present invention.
[0037] Figure 3 A comparison chart of the lift-to-drag ratio of the bionic airfoil and the basic airfoil provided in an embodiment of the present invention as a function of angle of attack. The results in the comparison chart show that the lift-to-drag ratio of the bionic airfoil of the present invention is significantly higher than that of the basic airfoil in the angle of attack range of 9° to 15°. The lift-to-drag ratios at angles of attack of 9° and 12° are 33.3 and 35, respectively, which are 7.1% and 75.4% higher than those of the basic airfoil, respectively. The optimization effect is best at an angle of attack of 15°, with the lift-to-drag ratio increased by 120.1% compared to the basic airfoil. The aerodynamic performance of the airfoil in this angle of attack range is greatly improved, which enables the aircraft to quickly obtain the required lift capability during the climb phase, and on the other hand, it can carry more weight at the same angle of attack.
[0038] Figure 4 V for the two airfoils at 9°, 12°, and 15° angles of attack x =0 isosurface (left side: basic airfoil, right side: bionic airfoil of the present invention). The area enclosed by the isosurface has a flow velocity opposite to the incoming flow, i.e., the recirculation zone. The smaller the recirculation zone, the better the aerodynamic performance of the airfoil. Numerical simulation results show that at angles of attack of 9°, 12°, and 15°, the recirculation zone area of the bionic airfoil is reduced by 53%, 66%, and 38%, respectively, compared to the basic airfoil. These results indicate that the bionic wing provided in this embodiment can effectively suppress flow separation within a certain range of angles of attack, reducing aircraft turbulence caused by unstable airflow and facilitating stable flight.
[0039] On the other hand, an aircraft is also provided, wherein the aircraft has the aircraft wing imitating the humpback whale flipper line.
[0040] While embodiments of the present invention have been shown and described, it will be appreciated by those skilled in the art that various changes, modifications, substitutions, and variations may be made to these embodiments without departing from the principles and spirit of the invention, and that the scope of the invention is defined by the appended claims and their equivalents.
Claims
1. An aircraft wing imitating the profile of a humpback whale flipper, comprising a wing body, characterized in that: The profile of the cross-sectional structure of the wing body is modeled after the flipper profile of a humpback whale, including an airfoil leading edge, an airfoil upper camber line, an airfoil lower camber line, and an airfoil trailing edge connected in a closed loop. A continuously undulating airfoil mid-camber line exists between the airfoil leading edge and the airfoil trailing edge. The maximum thickness of the wing body is located in the front half of the cross-sectional structure, and the maximum curvature of the wing body is located in the rear section of the cross-sectional structure and close to the airfoil trailing edge.
2. The aircraft wing imitating the humpback whale flipper line according to claim 1, characterized in that: The airfoil mid-camber line shows a trend of first rising, then falling, and then rising again from the leading edge of the airfoil to the trailing edge of the airfoil, and the amplitude of the first rising, then falling, and then rising increases successively.
3. The aircraft wing imitating the humpback whale flipper line according to claim 1, characterized in that: The airfoil camber line continuously fluctuates relative to the airfoil chord line of the wing body, and the maximum fluctuating height of the airfoil camber line relative to the airfoil chord line is the maximum camber position of the wing body.
4. The aircraft wing imitating the humpback whale flipper line according to claim 1, characterized in that: The maximum camber of the wing body is at a distance from the trailing edge of the airfoil that does not exceed 1 / 5 of the length of the airfoil chord of the wing body.
5. The aircraft wing imitating the humpback whale flipper line according to claim 1, characterized in that: The airfoil leading edge is the first 15% portion of the airfoil chord length of the wing body, and the airfoil trailing edge is the last 15% portion of the airfoil chord length of the wing body.
6. The aircraft wing imitating the humpback whale flipper line according to claim 1, characterized in that: The sizes and shapes of the airfoil leading edge, the airfoil upper camber line, the airfoil lower camber line, and the airfoil trailing edge satisfy the following relationship: r=4%C； t=19.95%C; X t =25.86%C; f=2.09%C; X f =86.88%C; Where r is the radius of the leading edge of the airfoil; t is the maximum thickness of the wing body; X t is the horizontal coordinate value corresponding to the maximum thickness position of the wing body; f is the maximum curvature of the wing body; X f is the horizontal coordinate value corresponding to the maximum curvature of the wing body; C is the length of the airfoil chord of the wing body.
7. The aircraft wing imitating the humpback whale flipper line according to claim 6, characterized in that: The camber line of the airfoil is distributed in a non-monotonic undulating manner along the length direction of the airfoil chord line, and three extreme camber points are formed at 6.07%C, 38.23%C and 86.88%C of the airfoil chord line, respectively. The three extreme camber points are 0.38%C, 0.94%C and 2.09%C, respectively. Among them, the 2.09%C position is the position where the maximum camber of the wing body is located.
8. The aircraft wing imitating the humpback whale flipper line according to claim 6, characterized in that: The shape of the cross-sectional structure is defined by given coordinate points. Assuming that the origin of the coordinates is located at the front end of the airfoil chord of the wing body, when the length of the airfoil chord is defined as C=1, the coordinate values corresponding to the upper and lower surfaces of the wing body are: ， Among them, X represents the horizontal coordinate and Y represents the vertical coordinate.
9. The aircraft wing imitating the humpback whale flipper line according to claim 6, characterized in that: The longitudinal length of the wing body is more than twice the length of the airfoil chord.
10. An aircraft, characterized in that: The aircraft has an aircraft wing imitating the humpback whale flipper profile according to any one of claims 1 to 9.