WO2020237850A1 - 一种仿生翼型叶片 - Google Patents

一种仿生翼型叶片 Download PDF

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WO2020237850A1
WO2020237850A1 PCT/CN2019/101758 CN2019101758W WO2020237850A1 WO 2020237850 A1 WO2020237850 A1 WO 2020237850A1 CN 2019101758 W CN2019101758 W CN 2019101758W WO 2020237850 A1 WO2020237850 A1 WO 2020237850A1
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Prior art keywords
curve
fish body
airfoil
bionic
point
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PCT/CN2019/101758
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English (en)
French (fr)
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燕浩
苏晓珍
张浩舟
李强
陈亮
王秀礼
柴立平
石海峡
夏巍
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合肥工业大学
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Publication of WO2020237850A1 publication Critical patent/WO2020237850A1/zh

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F03—MACHINES OR ENGINES FOR LIQUIDS; WIND, SPRING, OR WEIGHT MOTORS; PRODUCING MECHANICAL POWER OR A REACTIVE PROPULSIVE THRUST, NOT OTHERWISE PROVIDED FOR
    • F03B—MACHINES OR ENGINES FOR LIQUIDS
    • F03B3/00—Machines or engines of reaction type; Parts or details peculiar thereto
    • F03B3/12—Blades; Blade-carrying rotors
    • F03B3/121—Blades, their form or construction
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
    • Y02E10/00—Energy generation through renewable energy sources
    • Y02E10/20—Hydro energy
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
    • Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
    • Y02P70/50—Manufacturing or production processes characterised by the final manufactured product

Definitions

  • the invention belongs to the technical field of impeller design and production and processing, and specifically relates to a bionic airfoil blade designed with fish as a bionic object.
  • Bionics is developing from unilateral bionics to simultaneous multi-faceted bionics, from macro to micro, to a more precise direction; bionic technology is also being applied in engineering drag reduction and performance improvement. The increase, and good results have been achieved.
  • the development of bionic technology is also constantly advancing the change of the shape and structure of the impeller; the types of bionic objects are also increasing, among which fish is the most common one;
  • the Chinese patent document discloses a design method for a combined airfoil blade of a horizontal-axis tidal energy turbine. This method studies the hydrodynamic performance of a conventional airfoil and a bionic airfoil. The function of combining the conventional blade airfoil with the bionic airfoil, the purpose is to design a more superior combined airfoil blade; this method obtains the three-dimensional digital model of the fin and selects its cross-section at different positions The contour is used as the bionic fin airfoil.
  • the bionic fin airfoil is selected through analysis software, and the two-dimensional coordinates of the bionic airfoil and the required conventional airfoil are derived, and the leaf elements of the designed blade are optimized to obtain the parameters of each leaf element ,
  • the two-dimensional coordinates of the airfoil are converted into three-dimensional coordinate data. This method imports the three-dimensional coordinate data into the three-dimensional design software, performs lofting processing, and finally generates a combined airfoil blade.
  • the above method mainly uses fish fins as the bionic object to design bionic airfoil blades, but because the role of the fish fins in swimming is to maintain the balance of the fish's body, the fish fins are used as the bionic object for bionic airfoil blades
  • the design has limited help to improve the hydraulic performance of the bionic airfoil blade.
  • the technical problem to be solved by the present invention is to overcome the deficiencies in the prior art and provide a bionic airfoil blade with a fish body as a bionic object.
  • the above-mentioned bionic airfoil blade uses a fish body as a bionic object and corrects the head, fins and tail of the fish body.
  • the above-mentioned bionic airfoil blade has high hydraulic performance and lift-drag characteristics.
  • a bionic airfoil blade the profile curve of which includes the back curve of the bionic airfoil blade and the belly curve of the bionic airfoil blade;
  • the geometric parameters of the bionic airfoil blade are as follows:
  • ⁇ is the angle formed by the back curve of the bionic airfoil blade and the curve of the belly of the bionic airfoil blade at the leading edge;
  • ⁇ is the angle formed by the back edge of the bionic airfoil blade and the belly curve of the bionic airfoil blade.
  • the design method of the above-mentioned bionic airfoil blade includes the following steps:
  • Obtaining point cloud data scan the fish body to obtain a three-dimensional digital model, that is, point cloud data of the fish body, and import the point cloud data of the fish body into the reverse engineering software to obtain the three-dimensional fish body model;
  • step S3 Processing of contour curve: Based on the coordinate system established in step S2, the obtained fish contour curve is equally divided into k parts along the X axis, and k+1 abscissas including the origin are obtained on the X axis. A total of 2(k+1) coordinate points are acquired on the back curve of the fish body and the abdomen curve of the fish body, and the acquired coordinate points are processed without dimension to obtain the dimensionless coordinate points, and the dimensionless coordinate points are connected and performed sequentially Obtain a smooth fish body shape curve after smoothing;
  • Data correction Perform data correction according to the smooth fish body shape curve obtained after processing in step S3, including head data correction, fin data correction and tail data correction; after data correction, the contour curve of the bionic airfoil is obtained, and the bionic airfoil
  • the contour curve of the bionic airfoil includes the back curve of the bionic airfoil and the belly curve of the bionic airfoil.
  • the maximum thickness ⁇ max of the bionic airfoil is determined according to the contour curve of the bionic airfoil;
  • step S5 Based on the coordinate system of step S2, divide the contour curve of the bionic airfoil into a equal parts, and obtain a+1 abscissas including the origin on the X axis, the back curve of the bionic airfoil and the bionic wing A total of 2(a+1) coordinate points are acquired on the abdominal curve of the type, and the control point coordinates are calculated according to the acquired coordinate points and the maximum thickness ⁇ max acquired in step S4;
  • the specific steps of header data correction in step S4 are as follows:
  • the leading edge of the 791 airfoil is used as the origin of the coordinates, and the straight line between the leading edge and the trailing edge of the 791 airfoil is the X axis, to construct the 791 airfoil profile curve.
  • the leading edge of the 791 airfoil and the 791 The length of a straight line projected between any points on the profile curve of the airfoil on the X axis is x d ', and the chord length of the 791 airfoil is C;
  • the ratio of the length x d to the length of the fish body M of the straight line projected on the X axis between the tip of the anastomoses of the fish body and any point on the shape curve of the fish body is x d /M, and the fish body shape curve of the part where x d /M>0.2
  • the coordinate point data on the above remains unchanged, and the coordinate point data on the fish body profile curve of the part of x d /M ⁇ 0.2 is corrected: the coordinate point data of x d '/C ⁇ 0.2 on the profile curve of the 791 airfoil are replaced respectively
  • the specific steps of fin data correction in step S4 are as follows:
  • Pelvic fin data correction the intersection of the belly curve of the fish body and the contour curve of the fish abdomen fin produces two intersection points, namely intersection point A and intersection point B; define the straight line projection from the tip of the fish body to the intersection point A on the X axis
  • the length of is x q
  • the length of the straight line projected from the tip of the fish body to the point of intersection B on the X axis is x h
  • the straight line from the tip of the fish body to any point on the abdomen curve of the fish body is projected on the X axis
  • the length of is x a ;
  • the part of the abdomen curve of the fish body x q /M ⁇ x a /M ⁇ x h /M is smoothed by the arc method and combined with the change trend of the abdomen curve of the fish body;
  • the intersection of the back curve of the fish body and the contour curve of the back fin of the fish body produces two intersection points, namely intersection point C and intersection point D; define the straight line projection from the tip of the fish body to the intersection point C on the X axis
  • the length of is x q '
  • the length of the straight line projection from the tip of the fish body to the intersection point D on the X axis is x h '
  • the straight line projection from the tip of the fish body to any point on the abdomen curve of the fish body is on X
  • the length on the axis is x a '
  • the x q '/M ⁇ x a '/M ⁇ x h '/M part on the back curve of the fish body adopts the arc method and combines with the change trend of the back curve of the fish body for smooth processing.
  • the specific steps of the tail data correction in step S4 are as follows:
  • the projection length of the straight line from the tip of the fish head to any point of the fish body profile curve on the X axis is x d , where the data on the fish body profile curve for x d / M ⁇ 0.7 remains unchanged, and x d / M ⁇ 0.7
  • the data of is extended backward according to the streamline direction of the back curve of the fish body and the belly curve of the fish body.
  • the back curve of the fish body and the belly curve of the fish body produce an intersection on the side of the fish tail, and the intersection is rounded.
  • step S4 the specific steps of data correction in step S4 are as follows:
  • Head data correction Based on the 791 airfoil, the leading edge of the 791 airfoil is used as the origin of the coordinates, and the straight line between the leading edge and the trailing edge of the 791 airfoil is the X axis, to construct the 791 airfoil profile curve, 791 airfoil
  • the length of the straight line projected between the leading edge of and any point on the contour curve of the 791 airfoil on the X axis is x d ', and the chord length of the 791 airfoil is C;
  • the ratio of the length x d to the length of the fish body M of the straight line projected on the X axis between the tip of the anastomoses of the fish body and any point on the shape curve of the fish body is x d /M, and the fish body shape curve of the part where x d /M>0.2
  • the coordinate point data on the above remains unchanged, and the coordinate point data on the fish body profile curve of the part of x d /M ⁇ 0.2 is corrected: the coordinate point data of x d '/C ⁇ 0.2 on the profile curve of the 791 airfoil are respectively modified Replace the coordinate point data of x d /M ⁇ 0.2 on the contour curve of the fish body; the connection between the contour curve of the 791 airfoil and the contour curve of the fish body adopts the arc method to uniformly transition;
  • Fin data correction including dorsal fin data correction and pelvic fin data correction
  • Pelvic fin data correction the intersection of the belly curve of the fish body and the contour curve of the fish abdomen fin produces two intersection points, namely intersection point A and intersection point B; define the straight line projection from the tip of the fish body to the intersection point A on the X axis
  • the length of is x q , the length x h of the straight line projected from the tip of the fish body to the intersection point B on the X axis, the straight line from the tip of the fish body to any point on the abdomen curve of the fish body is projected on the X axis
  • the length of is x a ; the part of the abdomen curve of the fish body x q /M ⁇ x a /M ⁇ x h /M is smoothed by the arc method and combined with the change trend of the abdomen curve of the fish body;
  • the intersection of the back curve of the fish body and the contour curve of the back fin of the fish body produces two intersection points, namely intersection point C and intersection point D; define the straight line projection from the tip of the fish body to the intersection point C on the X axis
  • the length of is x q '
  • the length of the straight line projected from the tip of the fish body to the intersection D on the X axis is x h '
  • the straight line from the tip of the fish body to any point on the abdomen curve of the fish body is projected on X
  • the length on the axis is x a '
  • the x q '/M ⁇ x a '/M ⁇ x h '/M part on the back curve of the fish body adopts the arc method and combines the change trend of the back curve of the fish body for smooth processing;
  • Tail data correction the projection length of the straight line from the tip of the fish head to any point of the fish body profile curve on the X axis is x d , where the data on the fish body profile curve for x d / M ⁇ 0.7 remains unchanged, x d / The data of the part of M ⁇ 0.7 extends backward according to the streamline direction of the back curve of the fish body and the abdomen curve of the fish body. The back curve of the fish body and the abdomen curve of the fish body produce an intersection on the side of the fish tail. Fillet treatment.
  • the coordinate points on the back curve of the fish body and the abdomen curve of the fish body are non-dimensionally processed, and the coordinate points on the back curve of the fish body are defined as (x t , f u (x t )), and the fish
  • the coordinate point of the abdominal curve of the body is defined as (x t ,f l (x t ));
  • the dimensionless coordinate of the back curve is defined as (x t ,f' u (x t )), and the dimensionless coordinate of the abdominal curve is defined as (x t ,f' l (x t ))
  • the relationship between variables in dimensionless processing is defined as follows:
  • t represents the coordinate point on the X axis
  • u is the back curve of the fish body
  • l is the abdomen curve of the fish body
  • x t is the abscissa of the coordinate point on the back curve of the fish body and the abdomen curve of the fish body
  • M is Fish body length
  • f u (x t ) is the ordinate on the back curve of the fish body at x t
  • f l (x t ) is the ordinate on the abdomen curve of the fish body at x t
  • x t is the abscissa of the longitudinal dimension of fish coordinate.
  • the formula for calculating the control point coordinates in the step S5 is as follows:
  • f u (x i ) is the ordinate on the back curve of the airfoil at point x i
  • fl(x i ) is the ordinate on the abdomen curve of the airfoil at point x i
  • Is the ordinate of the control point on the abdomen curve of the bionic airfoil
  • is the ordinate of the control point on the back curve of the bionic airfoil
  • ⁇ max is the maximum thickness of the bionic airfoil.
  • the step S1 adopts m fish bodies to scan, and each fish body is scanned n times to obtain a total of m ⁇ n sets of data , Obtain a total of m ⁇ n fish body contour curves, perform S3 processing on m ⁇ n fish body contour curves to obtain dimensionless coordinates, and perform data fitting on the dimensionless coordinates to obtain a smooth fish body contour curve.
  • the data fitting adopts the least square method for fitting, and the specific fitting method is as follows:
  • x i is the abscissa on the X axis
  • f(x i ) represents the ordinate on the back curve of the fish body or the abdomen curve of the fish body when the abscissa is x i
  • To obtain the average value of the abscissa x i in the m ⁇ n group of data It is the average value of the ordinates on the back curve of the fish body or the belly curve of the fish body when the abscissa is x i ; Is the average value of all abscissas when i in abscissa x i takes a value from 1 to j, Is the abscissa Time is the ordinate on the curve of the back of the fish body or on the curve of the abdomen of the fish body.
  • the bionic airfoil blade designed by the design method of the present invention has better lift and drag characteristics and hydraulic performance
  • the lift coefficient of the bionic airfoil blade designed by the design method is greater than NACA0012 airfoil and NACA0015 airfoil before reaching the stall angle of attack; its drag coefficient increases correspondingly with the increase of the stall angle of attack, the design in the present invention
  • the drag coefficient of the bionic airfoil blade designed by the method is less than NACA0012 airfoil and NACA0015 airfoil before reaching the stall angle of attack; and the bionic airfoil blade designed by the design method of the present invention has an attack angle of 5°, 10° At 15°, the pressure difference between the upper and lower airfoil surfaces is greater than that of NACA0012 airfoil and NACA0015 airfoil. Therefore, the bionic airfoil blade designed in the present invention can generate greater lift;
  • the data is corrected according to the physiological characteristics of the bionic object.
  • the fish body is used as the bionic object, because the role of the fish mouth is to better
  • the geometry of the mouth does not contribute much to the hydraulic characteristics of the airfoil.
  • the design method of the present invention is based on the 791 airfoil, and the data of the 791 airfoil with x d /C ⁇ 0.2 is used in the bionic of the present invention.
  • the influence of the geometry of the fish's mouth on the hydraulic characteristics of the bionic airfoil blade is avoided, and the hydraulic performance and lift-drag characteristics of the bionic airfoil blade are further improved;
  • the design method of the present invention also affects the fin data of the fish body. Make corrections so that the back curve of the fin part of the bionic airfoil and the belly curve of the bionic airfoil are smoothed using the arc method and combined with the change trend of the back curve and the belly curve.
  • the smoothed bionic airfoil has the back and belly curves combined There is no fish fin structure, which improves the hydraulic characteristics and lift-drag performance of the bionic airfoil blade;
  • the main purpose of the fish tail is to push the body forward and control the direction, maintain the balance of the fish body, and make little contribution to the hydraulic performance of the bionic airfoil. Therefore, the design method of the present invention corrects the data of the tail.
  • the tail of the bionic airfoil extends backwards according to the streamline direction of the back curve of the bionic airfoil and the abdomen curve of the bionic airfoil.
  • the back curve and the belly curve produce an intersection on the right side of the fish body. The intersection is rounded. Therefore, through correction In the future, the tail of the bionic airfoil blade will have a smooth rounded structure, which enhances the hydraulic characteristics and lift-drag performance of the bionic airfoil blade;
  • the design method of the present invention in the smoothing process of the contour curve of the fish body model, the coordinate points on the back curve and the abdomen curve of the fish body model are non-dimensionally processed, which avoids the fish body from being scanned during the scanning process.
  • the difference in fish body size and scanning position causes the problem of large errors in the bionic airfoil blade of the component, which improves the accuracy of constructing the bionic airfoil blade by the design method of the present invention; in addition, the smoothing of the curve makes The designed bionic airfoil surface is smooth, which reduces the resistance of the designed bionic airfoil blade in the fluid.
  • the design method of the present invention constructs the control point coordinates, and its purpose is to calculate the bionic airfoil blades of different thicknesses and sizes, and determine the maximum thickness of the bionic airfoil blade according to the completed control point coordinates and the design requirements Calculate the coordinate points of the back curve and belly curve of the bionic airfoil blade to be designed, and it is convenient to import engineering software for lofting processing to design the required bionic airfoil blade, which has wide applicability and strong practicability.
  • Figure 1 is a schematic diagram of the structure of the present invention
  • Figure 2 is a schematic diagram of the structure of the sturgeon model in the present invention.
  • FIG. 9 is a comparison diagram of the pressure curves of the bionic airfoil blade and NACA0012 airfoil and NACA0015 airfoil in a fluid with a Reynolds number of 3E6; where the power angle is 5°;
  • Fig. 10 is a comparison diagram of the pressure curves of the bionic airfoil blade and NACA0012 airfoil and NACA0015 airfoil in a fluid with a Reynolds number of 3E6; where the power angle is 10°;
  • 11 is a comparison diagram of the pressure curves of the bionic airfoil blade and NACA0012 airfoil and NACA0015 airfoil in a fluid with a Reynolds number of 3E6; where the power angle is 15°;
  • Figure 12 is a comparison diagram of the pressure curves of the bionic airfoil blade and NACA0012 airfoil and NACA0015 airfoil in a fluid with a Reynolds number of 3E6; where the power angle is 20°.
  • This embodiment uses a sturgeon as the acquisition model of the bionic airfoil blade, and the specific operation method in this embodiment is also applicable to other fish bodies for bionic airfoil acquisition and the design of airfoil blades.
  • the bionic airfoil blade designed based on sturgeon as a bionic object its profile curves include the back curve of the bionic airfoil blade and the belly curve of the bionic airfoil blade, the back curve of the bionic airfoil blade and the belly curve of the bionic airfoil blade Intersection points are generated at the two ends.
  • the linear distance between the two said intersection points is the chord length of the airfoil, and the maximum distance between the back curve of the bionic airfoil blade and the curve of the belly of the bionic airfoil blade is the maximum thickness of the bionic airfoil blade ⁇ max ;
  • step S1 in order to reduce the influence of scanning errors on the accuracy of the construction of the sturgeon model, m sturgeons are selected for scanning, and each sturgeon is scanned n times to obtain m ⁇ n sets of data;
  • step S1 the accuracy of the 3D scanner is 0.03mm
  • a two-dimensional sturgeon fish body contour curve is constructed based on the three-dimensional fish body model obtained in step S1, and the contour curve includes the sturgeon The back curve of the fish body and the abdomen curve of the sturgeon body; the length of the sturgeon body length M from the sturgeon tip to the tail tip of the sturgeon model is projected on the X axis;
  • step S3 Processing of contour curve: Based on the coordinate system established in step S2, the obtained sturgeon body contour curve is evenly divided into k parts along the X axis, and k+1 horizontal lines including the origin are obtained on the X axis. Coordinates, a total of 2(k+1) coordinate points are obtained on the back curve of the sturgeon body and the belly curve of the sturgeon body.
  • the coordinates of the back curve of the sturgeon body are defined as (x s ,f u (x s )), the coordinate point of the abdomen curve of the sturgeon body is defined as (x s ,f l (x s )); the acquired coordinate points are processed without dimension to obtain the dimensionless coordinate point, and the back curve of the sturgeon body is infinite Dimensional coordinates are defined as (x s ,f' u (x s )), and the dimensionless coordinate points of the abdomen curve of sturgeon fish are defined as (x s ,f' l (x s )), and the dimensionless coordinate points are sequentially After connecting and smoothing, a smooth sturgeon body shape curve is obtained; the relationship between variables in the dimensionless processing is defined as follows:
  • t represents the coordinate point on the X axis
  • u is the back curve of the sturgeon fish body
  • l is the abdomen curve of the sturgeon fish body
  • x t is the back curve of the sturgeon fish body and the coordinates on the abdomen curve of the fish body abscissa points
  • M being the length of the fish
  • f u (x t) as abscissa and ordinate of the curve of the back body sturgeon at x t
  • f l (x t) is at the abscissa x t sturgeon the ordinate on the curve of the abdomen of the fish body
  • f 'u (x t) as abscissa and the ordinate is a dimensionless graph sturgeon on the back body at x t
  • f' l (x t) is the abscissa
  • M is the length of
  • step S1 Since in step S1, in order to reduce the influence of the scanning error on the accuracy of the construction of the sturgeon model, m sturgeons are selected for scanning, and each sturgeon is scanned n times, so in step S2, a total of m ⁇ n sturgeon fish are obtained Body shape curve.
  • step S3 2(k+1) coordinate points can be acquired on each sturgeon body shape curve, and the coordinate points are processed without dimension to obtain the dimensionless coordinate points.
  • the least squares method is used for data fitting. After fitting, a sturgeon body shape curve is formed, and the sturgeon body shape curve tends to be smooth.
  • the specific fitting method is as follows:
  • x i is the abscissa on the X axis
  • f(x i ) represents the ordinate of the back curve of the sturgeon body when the abscissa is x i
  • Is the average value of all abscissas when i in abscissa x i takes a value from 1 to j
  • Is the abscissa Time is located on the ordinate on the back curve of the sturgeon body
  • x i is the abscissa on the X axis
  • f(x i ) represents the ordinate of the abdomen curve of the sturgeon body when the abscissa is x i
  • Is the average value of all abscissas when i in abscissa x i takes a value from 1 to j
  • Is the abscissa Time is located on the ordinate on the curve of the abdomen of the sturgeon body
  • step S1 3 sturgeons are selected for scanning in step S1, and each sturgeon is scanned 3 times to obtain a total of 9 sets of data.
  • the value of j is 9;
  • step S4 Data correction: According to the smooth sturgeon body shape curve obtained after the processing of step S3, data are corrected, including head data correction, fin data correction and tail data correction; after data correction, the contour curve of the bionic airfoil is obtained, which is bionic
  • the profile curve of the airfoil includes the back curve of the bionic airfoil and the belly curve of the bionic airfoil.
  • the maximum thickness ⁇ max of the bionic airfoil is determined according to the profile curve of the bionic airfoil;
  • the leading edge of the 791 airfoil is used as the origin of the coordinates, and the straight line between the leading edge and the trailing edge of the 791 airfoil is the X axis, to construct the 791 airfoil profile curve.
  • the leading edge of the 791 airfoil and the 791 The length of a straight line projected between any points on the profile curve of the airfoil on the X axis is x d ', and the chord length of the 791 airfoil is C;
  • the ratio of the length x d of the sturgeon fish body's snout tip to any point on the sturgeon body contour curve on the X axis and the sturgeon body length M is x d /M, x d /M>0.2
  • the coordinate point data on part of the sturgeon body contour curve remains unchanged, and the coordinate point data on the sturgeon body contour curve of the part of x d /M ⁇ 0.2 is corrected: x d' on the contour curve of the 791 airfoil
  • the coordinate point data of /C ⁇ 0.2 replaces the coordinate point data of x d /M ⁇ 0.2 on the contour curve of the sturgeon body; the connection between the contour curve of the 791 airfoil and the contour curve of the sturgeon body adopts the arc method to uniformly pass .
  • Fin data correction includes dorsal fin data correction and pelvic fin data correction
  • Pelvic fin data correction The intersection of the belly curve of the sturgeon body and the contour curve of the sturgeon body's abdomen fin produces two intersection points, namely intersection point A and intersection point B; define the distance between sturgeon body mastoid tip and intersection point A
  • the length of the straight line projection on the X axis is x q
  • the length of the straight line projection on the X axis from the tip of the sturgeon body to the intersection point B is x h
  • the length of a straight line projected at any point on the abdomen curve on the X-axis is x a ;
  • the x q /M ⁇ x a /M ⁇ x h /M part of the sturgeon body's abdomen curve adopts the arc method and combines the sturgeon fish
  • the trend of the body's abdominal curve is smoothed;
  • the intersection of the back curve of the sturgeon body and the contour curve of the back fin of the sturgeon body produces two intersection points, namely intersection point C and intersection point D; define the distance between the sturgeon body muzzle tip and intersection point C
  • the length of the straight line projection on the X axis is x q '
  • the length of the straight line projection on the X axis from the tip of the sturgeon body to the point of intersection D is x h '
  • the length of the sturgeon body from the tip of the sturgeon to the sturgeon The length of a straight line projected on the X axis of any point on the curve of the abdomen of the body is x a '
  • the back curve of the sturgeon body is x q '/M ⁇ x a '/M ⁇ x h '/M part adopts a circular arc
  • the method is combined with the change trend of the sturgeon body's back curve for smoothing;
  • the projection length of the straight line from the sturgeon fish body to any point on the sturgeon body contour curve on the X axis is x d , where the data on the sturgeon body contour curve for x d /M ⁇ 0.7 remains unchanged, x
  • the data of d /M ⁇ 0.7 extends backward according to the streamline direction of the back curve of the sturgeon body and the abdomen curve of the sturgeon body.
  • the back curve of the sturgeon body and the abdomen curve of the sturgeon body are in the tail.
  • An intersection is generated on one side, and the intersection is rounded.
  • step S5 Based on the coordinate system of step S2, the profile curve of the bionic airfoil is evenly divided into a parts, and a+1 abscissas including the origin are obtained on the X axis, the back curve of the bionic airfoil and the bionic A total of 2(a+1) coordinate points are acquired on the abdomen curve of the airfoil, and the control point coordinates are calculated according to the acquired coordinate points and the maximum thickness ⁇ max acquired in step S4;
  • the control point coordinates include the control point coordinates of the bionic airfoil back curve (x d ,
  • the calculation formula is as follows:
  • f u (x i ) is the ordinate on the back curve of the airfoil at point x i
  • fl(x i ) is the ordinate on the abdomen curve of the airfoil at point x i
  • Is the ordinate of the control point on the abdomen curve of the bionic airfoil
  • is the ordinate of the control point on the back curve of the bionic airfoil
  • ⁇ max is the maximum thickness of the bionic airfoil.
  • a k, where, when the value of a is 20, the control point coordinates are shown in Table 1;
  • Sturgeon hydrofoil stands for sturgeon bionic airfoil blade.
  • the lift coefficient of the sturgeon airfoil blade increases with the increase of the stall angle of attack. Before the sturgeon airfoil blade reaches the stall angle of attack, the lift coefficient is greater than the NACA0012 airfoil and NACA0015 airfoil;
  • Reynolds numbers Re 1E6, 3E6 and 5E6
  • the drag coefficient of the sturgeon airfoil blade increases with the increase of the stall angle of attack. Before the sturgeon airfoil blade reaches the stall angle of attack, the drag coefficient is less than the NACA0012 airfoil and NACA0015 airfoil;
  • the results show: NACA0012 airfoil and NACA0015 airfoil have a similar trend in the same area, that is, as the angle of attack increases, the pressure difference between the upper and lower airfoils increases, resulting in greater lift; the sturgeon airfoil blade is more than the NACA0012 airfoil and NACA0015 airfoil.
  • the angle of attack When the angle of attack is 5°, 10° and 15°, it produces greater lift, especially in the area of maximum thickness, but this area may also cause cavitation; because the angle of attack is 20° larger than the sturgeon airfoil in BMW
  • the number Re the stall angle of attack under the condition of 3E6, the stall angle of attack of the sturgeon airfoil can be checked in the previous text, and the pressure difference between the upper and lower airfoils suddenly decreases;

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Abstract

一种仿生翼型叶片，其外形曲线包括仿生翼型叶片背部曲线和仿生翼型叶片腹部曲线，仿生翼型叶片背部曲线和仿生翼型叶片腹部曲线在前缘形成的夹角α为14.43 ゜，其在后缘形成的夹角β为6.42 ゜。还披露了一种仿生翼型叶片的设计方法。该仿生翼型叶片具有较好的升阻特性和水力性能，该设计方法可设计不同最大厚度的仿生翼型，实用性强。

Description

一种仿生翼型叶片
本申请主张2019年5月27日申请的申请号为201910447135.5的“一种仿生翼型叶片”的优先权，原受理机构为中国。
技术领域
本发明属于叶轮设计及生产加工技术领域，具体地说，涉及一种以鱼类作为仿生对象进行设计的一种仿生翼型叶片。
背景技术
仿生学正从生物单方面仿生向同时向多个方面耦合仿生的方向发展，从宏观到微观，向更加精密的方向发展；仿生技术同时在工程减阻，性能提升等方面的应用研究也在不断增多，也取得了不错的效果，仿生技术的发展也在不断推进叶轮的形貌和结构发生改变；仿生对象的种类也在不短增多，其中鱼类是最为常见的一种仿生对象；
中国专利文献(申请公布号：CN105201728A)公开了一种水平轴潮流能水轮机组合翼型叶片的设计方法，该方法分别研究常规翼型及仿生翼型的水动力性能，根据各叶素在叶片中的作用，将常规的叶片翼型与仿生翼型相结合，其目的旨在设计性能更为优越的组合翼型叶片；该方法通过获取鱼鳍的三维数字模型，选取其不同位置处的横截面轮廓作为仿生鱼鳍翼型，通过分析软件选取仿生鱼鳍翼型，并导出仿生翼型和所需常规翼型的二维坐标，对设计叶片的叶素进行优化，得到每个叶素的参数，将翼型的二维坐标转换为三维坐标数据，该方法将得到三维坐标数据导入到三维设计软件中，进行放样处理，最终生成组合翼型叶片。上述方法主要采用鱼鳍作为仿生对象进行设计仿生翼型叶片，但是由于鱼类在游弋中鱼鳍所起的作用是用来维持鱼类身体的平衡，以鱼鳍作为仿生对象进行仿生翼型叶片的设计对提高仿生翼型叶片水力性能的帮助有限。
发明内容
本发明要解决的技术问题为克服现有技术中的不足之处，提供一种以鱼体作为仿生对象的仿生翼型叶片。上述仿生翼型叶片是以鱼体作为仿生对象并且对鱼体的头部、鱼鳍以及尾部进行修正，上述的仿生翼型叶片具有较高的水力性能和升阻特性。
为实现上述目的，本发明采用了以下技术方案：
一种仿生翼型叶片，其外形曲线包括仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线；
所述仿生翼型叶片的几何参数如下：
α＝14.43°；
β＝6.42°；
式中，α为仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线在前缘形成的夹角；
β为仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线在后缘形成的夹角。
优选地，上述仿生翼型叶片的设计方法，包括以下步骤：
S1、点云数据的获取：对鱼体进行扫描获取三维数字模型，即鱼体的点云数据，将鱼体的点云数据导入到逆向工程软件中获取三维鱼体模型；
S2、构建鱼体外形曲线以及确定鱼体长度M：建立坐标系，以鱼体吻突尖端作为坐标原点，以鱼体吻突尖端到鱼体以及鱼尾连接处的中心点之间的直线为X轴，根据步骤S1获取的三维鱼体模型为基础构建二维的鱼体外形曲线，其外形曲线包括鱼体的背部曲线和鱼体的腹部曲线；鱼体模型的吻突尖端到尾部尖端的直线投影在X轴上的长度即为鱼体长度M；
S3、外形曲线的处理：以步骤S2建立的坐标系为基础，将获取的鱼体外形曲线沿X轴均匀等分k份，在X轴上获取包括原点在内的k+1个横坐标，鱼体的背部曲线以及鱼体的腹部曲线上共获取2(k+1)个坐标点，对获取的坐标点进行无量纲处理，得到无量纲坐标点，无量纲坐标点之间依次连接并进行光滑处理后获取光滑的鱼体外形曲线；
S4、数据修正：根据步骤S3处理后得到光滑的鱼体外形曲线进行数据修正，包括头部数据修正、鱼鳍数据修正和尾部数据修正；数据修正后得到仿生翼型的外形曲线，仿生翼型的外形曲线包括仿生翼型的背部曲线和仿生翼型的腹部曲线，根据仿生翼型的外形曲线确定仿生翼型的最大厚度δ max；
S5、以步骤S2的坐标系为基础，将仿生翼型的外形曲线均匀等分a份，在X轴上获取包括原点在内的a+1个横坐标，仿生翼型的背部曲线以及仿生翼型的腹部曲线上共获取2(a+1)个坐标点，根据获取的坐标点以及步骤S4中获取的最大厚度δ max计算控制点坐标；
S6、仿生翼型叶片的建立：根据设计要求确定仿生翼型叶片的最大厚度，根据最大厚度以及控制点坐标计算仿生翼型叶片背部曲线上的坐标点以及仿生翼型叶片腹部曲线上的坐标点，将上述计算后得到的坐标点导入到三维设计软件中进行放样处理，生成仿生翼型叶片。
优选地，所述步骤S4中头部数据修正的具体步骤如下：
以791翼型为基础，以791翼型前缘为坐标原点，791翼型的前缘与后缘之间的直线为X轴，构建791翼型的外形曲线，791翼型的前缘与791翼型的外形曲线上任意一点之间的直线投影在X轴上的长度为x d’，791翼型的弦长为C；
鱼体的吻突尖端与鱼体外形曲线上任意一点的直线投影在X轴上的长度x d与鱼体长度M 的比为x d/M，x d/M＞0.2部分的鱼体外形曲线上的坐标点数据不变，对x d/M≤0.2部分的鱼体外形曲线上的坐标点数据进行修正：将791翼型的外形曲线上x d’/C≤0.2的坐标点数据分别替换鱼体外形曲线上x d/M≤0.2的坐标点数据；791翼型的外形曲线与鱼体外形曲线的连接处采用圆弧法均匀过度。
优选地，所述步骤S4中鱼鳍数据修正的具体步骤如下：
腹鳍数据修正：鱼体的腹部曲线与鱼体腹部鱼鳍的外形曲线相交产生两个交点，分别为交点A和交点B；定义鱼体吻突尖端到交点A之间的直线投影在X轴上的长度为x q，鱼体吻突尖端到交点B之间的直线投影在X轴上的长度为x h，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a；鱼体的腹部曲线上x q/M≤x a/M≤x h/M部分采用圆弧法并结合鱼体的腹部曲线变化趋势进行光滑处理；
背鳍数据修正：鱼体的背部曲线与鱼体背部鱼鳍的外形曲线相交产生两个交点，分别为交点C和交点D；定义鱼体吻突尖端到交点C之间的直线投影在X轴上的长度为x q’，鱼体吻突尖端到交点D之间的直线投影在X轴上的长度为x h’，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a’；鱼体的背部曲线上x q’/M≤x a’/M≤x h’/M部分采用圆弧法并结合鱼体的背部曲线变化趋势进行光滑处理。
优选地，所述步骤S4中尾部数据修正的具体步骤如下：
鱼头吻突尖端到鱼体外形曲线任何一点的直线在X轴上投影的长度为x d，其中鱼体外形曲线上x d/M＜0.7部分的数据不变，x d/M≥0.7部分的数据按照鱼体的背部曲线以及鱼体的腹部曲线的流线方向向后延伸，鱼体的背部曲线以及鱼体的腹部曲线在鱼尾一侧产生一个交点，对交点处进行圆角处理。
进一步优选地，所述步骤S4中数据修正的具体步骤如下：
头部数据修正：以791翼型为基础，以791翼型前缘为坐标原点，791翼型的前缘与后缘之间的直线为X轴，构建791翼型的外形曲线，791翼型的前缘与791翼型的外形曲线上任意一点之间的直线投影在X轴上的长度为x d’，791翼型的弦长为C；
鱼体的吻突尖端与鱼体外形曲线上任意一点的直线投影在X轴上的长度x d与鱼体长度M的比为x d/M，x d/M＞0.2部分的鱼体外形曲线上的坐标点数据不变，对x d/M≤0.2部分的鱼体外形曲线上的坐标点数据进行修正：将791翼型的外形曲线上x d’/C≤0.2的的坐标点数据分别替换鱼体外形曲线上x d/M≤0.2的坐标点数据；791翼型的外形曲线与鱼体外形曲线的连接处采用圆弧法均匀过度；
鱼鳍数据修正，包括背鳍数据修正和腹鳍数据修正；
腹鳍数据修正：鱼体的腹部曲线与鱼体腹部鱼鳍的外形曲线相交产生两个交点，分别为 交点A和交点B；定义鱼体吻突尖端到交点A之间的直线投影在X轴上的长度为x q，鱼体吻突尖端到交点B之间的直线投影在X轴上的长度的x h，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a；鱼体的腹部曲线上x q/M≤x a/M≤x h/M部分采用圆弧法并结合鱼体的腹部曲线变化趋势进行光滑处理；
背鳍数据修正：鱼体的背部曲线与鱼体背部鱼鳍的外形曲线相交产生两个交点，分别为交点C和交点D；定义鱼体吻突尖端到交点C之间的直线投影在X轴上的长度为x q’，鱼体吻突尖端到交点D之间的直线投影在X轴上的长度的x h’，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a’；鱼体的背部曲线上x q’/M≤x a’/M≤x h’/M部分采用圆弧法并结合鱼体的背部曲线变化趋势进行光滑处理；
尾部数据修正：鱼头吻突尖端到鱼体外形曲线任何一点的直线在X轴上投影的长度为x d，其中鱼体外形曲线上x d/M＜0.7部分的数据不变，x d/M≥0.7部分的数据按照鱼体的背部曲线以及鱼体的腹部曲线的流线方向向后延伸，鱼体的背部曲线以及鱼体的腹部曲线在鱼尾一侧产生一个交点，对交点处进行圆角处理。
优选地，所述步骤S3中对鱼体背部曲线以及鱼体的腹部曲线上的坐标点进行无量纲处理，鱼体的背部曲线坐标点定义为(x t,f u(x t))，鱼体的腹部曲线坐标点定义为(x t,f l(x t))；背部曲线无量纲坐标定义为(x t,f’ u(x t))，腹部曲线无量纲坐标定义为(x t,f’ l(x t))，无量纲处理中变量之间的关系定义如下：
Figure PCTCN2019101758-appb-000001
式中t代表X轴上的坐标点，u为鱼体的背部曲线，l为鱼体的腹部曲线，x t为鱼体的背部曲线以及鱼体的腹部曲线上坐标点的横坐标，M为鱼体长度；f u(x t)为横坐标为x t处鱼体的背部曲线上的纵坐标，f l(x t)为横坐标为x t处鱼体的腹部曲线上的纵坐标；f’ u(x t)为横坐标为x t处鱼体的背部曲线上的无量纲纵坐标，f’ l(x t)为横坐标为x t处鱼体的腹部曲线上的无量纲纵坐标。
优选地，所述步骤S5中计算控制点坐标的公式如下：
|f l(x d)|＝f l(x i)/δ max，|f u(x d)|＝f u(x i)/δ max
式中：f u(x i)为x i点处翼型背部曲线上的纵坐标，fl(x i)为x i点处翼型腹部曲线上的纵坐标，|f l(x d)|为仿生翼型腹部曲线上的控制点纵坐标，|f u(x d)|为仿生翼型背部曲线上的控制点纵坐标，δ max为仿生翼型的最大厚度。
进一步优选地，为了降低鱼体扫描的误差给仿生翼型叶片设计时造成的不便，所述步骤 S1采用m只鱼体进行扫描，且每只鱼体扫描n次，共获取m×n组数据，共获取m×n条鱼体外形曲线，对m×n条鱼体外形曲线进行S3步骤处理获取无量纲坐标，对无量纲坐标进行数据拟合，获取一条光滑的鱼体外形曲线。
优选地，所述的数据拟合采用最小二乘法进行拟合，具体的拟合方式如下：
f(x)＝b 0+b 1x
其中：
Figure PCTCN2019101758-appb-000002
Figure PCTCN2019101758-appb-000003
式中：
Figure PCTCN2019101758-appb-000004
由于选取m只鱼体进行扫描，且每只鱼体扫描n次，共获取m×n组数据，因此，j取值为m×n；式中：b 0与b 1为常数；
x i为X轴上的横坐标，f(x i)分别代表横坐标为x i时位于鱼体的背部曲线或鱼体的腹部曲线上的纵坐标；
Figure PCTCN2019101758-appb-000005
为获取m×n组数据中横坐标x i的平均值；
Figure PCTCN2019101758-appb-000006
为横坐标为x i时分别位于鱼体的背部曲线或者鱼体的腹部曲线上的纵坐标的平均值；
Figure PCTCN2019101758-appb-000007
为横坐标x i中i取值从1到j时所有横坐标的平均值，
Figure PCTCN2019101758-appb-000008
为横坐标为
Figure PCTCN2019101758-appb-000009
时位于鱼体的背部曲线上或鱼体的腹部曲线上的纵坐标。
相比于现有技术，本发明的有益效果为：
(1)通过本发明中的设计方法设计出的仿生翼型叶片具有较好的升阻特性和水力性能；
在不同雷诺数的流体中，上述的仿生翼型叶片升力系数随着随着失速攻角的增大相应增大，以水动力性能优越的NACA0012翼型及NACA0015翼型作为比较，本发明中的设计方法设计出的仿生翼型叶片在达到失速攻角前，升力系数均大于NACA0012翼型及NACA0015翼型；其阻力系数随着随着失速攻角的增大相应增大，本发明中的设计方法设计出的仿生翼型叶片在达到失速攻角前，阻力系数均小于NACA0012翼型及NACA0015翼型；且通过本发明中的设计方法设计出的仿生翼型叶片在攻角5°、10°和15°时，其上下翼面的压力差大于NACA0012翼型及NACA0015翼型的压力差，因此，本发明中设计的仿生翼型叶片能够产生更大的升力；
(2)通过本发明中的设计方法在设计仿生翼型叶片过程中，根据仿生对象的生理特性进行数据修正，本发明中采用鱼体作为仿生对象，由于鱼类嘴部的作用是为了更好地寻觅食物，其嘴部几何结构对翼型的水力特性贡献不大，本发明中的设计方法以791翼型为基础，将x d/C≤0.2的791翼型的数据用到本发明仿生翼型叶片上，避免了鱼类嘴部几何结构对仿生翼型叶片水力特性的影响，进一步提高了仿生翼型叶片的水力性能和升阻特性；
(3)由于鱼类在游弋中，鱼鳍主要用来保持游弋过程中的平衡性，鱼鳍对翼型的水力特性贡献不大，因此本发明中的设计方法还对鱼体的鱼鳍数据进行修正，使得鱼鳍部分仿生翼型背部曲线和仿生翼型腹部曲线采用圆弧法并结合背部曲线和腹部曲线的变化趋势进行光滑处理，光滑处理后的仿生翼型其背部曲线以及腹部曲线并没有鱼类的鳍状结构，提升了仿生翼型叶片的水力特性和升阻性能；
(4)鱼类的尾部其主要目的是推动身体前进和控制方向，保持鱼体的平衡，对仿生翼型的水力性能贡献不大，因此，本发明中的设计方法对尾部的数据进行修正，仿生翼型尾部按照仿生翼型背部曲线以及仿生翼型腹部曲线的流线方向向后延伸，背部曲线以及腹部曲线在鱼体右侧产生一个交点，对交点处进行圆角处理，因此，通过修正以后仿生翼型叶片其尾部为光滑的圆角结构，增强了仿生翼型叶片的水力特性和升阻性能；
(5)本发明中的设计方法在在鱼体模型的外形曲线光滑处理过程中，对鱼体模型的背部曲线以及腹部曲线上的坐标点采用无量纲处理，避免了鱼体在扫描过程中由于鱼体大小尺寸以及扫描位置的不同导致构件的仿生翼型叶片误差较大的问题发生，提高了通过本发明中的设计方法构建仿生翼型叶片的准确性；另外，通过对曲线的光滑处理使得设计的仿生翼型表面光滑，降低了设计的仿生翼型叶片在流体中的阻力。
(6)本发明中的设计方法构建控制点坐标，其目的是适用于计算不同厚度设计不同尺寸的仿生翼型叶片，根据构建完成的控制点坐标以及按照设计要求确定仿生翼型叶片的最大厚度和计算公式，计算需要设计的仿生翼型叶片背部曲线和腹部曲线的坐标点，方便导入工程软件进行放样处理从而设计出需要的仿生翼型叶片，其适用性广，实用性强。
(7)本发明中的设计方法在设计仿生翼型叶片的过程中，通过对多只鱼体进行扫描，且每只鱼体扫描多次，再进行本发明中上述步骤的操作，进而得到多组控制点坐标，对控制点坐标进行求平均处理，大大降低了仿生翼型叶片在设计过程中存在的误差，使得设计出的仿生翼型叶片具有良好的水力特性和升阻性能。
附图说明
图1为本发明的结构示意图；
图2为本发明中鲟鱼模型的结构示意图；
图3为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型升力系数比较图；其中，雷诺数Re＝1E6；
图4为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型升力系数比较图；其中，雷诺数Re＝3E6；
图5为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型升力系数比较图；其中，雷诺数Re＝5E6；
图6为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型阻力系数比较图；其中，雷诺数Re＝1E6；
图7为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型阻力系数比较图；其中，雷诺数Re＝3E6；
图8为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型阻力系数比较图；其中，雷诺数Re＝5E6；
图9为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型在雷诺数为3E6流体中压力曲线比较图；其中，功角为5°；
图10为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型在雷诺数为3E6流体中压力曲线比较图；其中，功角为10°；
图11为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型在雷诺数为3E6流体中压力曲线比较图；其中，功角为15°；
图12为本发明中仿生翼型叶片与NACA0012翼型以及NACA0015翼型在雷诺数为3E6流体中压力曲线比较图；其中，功角为20°。
具体实施方式
为使本发明的目的、技术方案和优点更加清楚，下面结合附图通过特定的实施例进一步说明本发明的实施方式。
本实施例采用鲟鱼作为仿生翼型叶片的获取模型，该实施例中的具体操作方法同样适用于其他鱼体用于仿生翼型的获取以及翼型叶片的设计。
如图1所示，基于鲟鱼作为仿生对象设计的仿生翼型叶片，其外形曲线包括仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线，仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线两端产生交点，两个所述的交点之间的直线距离为翼型的弦长，且仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线之间的最大距离为仿生翼型叶片的最大厚度δ max；
如图1所示，所述仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线在前缘形成的夹角 为α，α＝14.43°；所述仿生翼型叶片背部曲线以及仿生翼型曲线在后缘形成夹角为β，β＝6.42°。
上述仿生翼型叶片的设计方法，具体步骤如下：
S1、点云数据的获取：将完整的鲟鱼鱼体自由伸展并固定在用非接触式3D激光扫描仪的圆桌上，在鲟鱼的身体四周贴上用于采集数据的贴片，三维扫描仪进行扫描获取鲟鱼的点云数据，将获取的点云数据导入Geomagic Design X工程软件后获取三维鲟鱼模型；
上述S1步骤中，为了降低扫描的误差对构建鲟鱼模型准确性的影响，选取m只鲟鱼进行扫描，且每只鲟鱼扫描n次，获取m×n组数据；
上述S1步骤中，三维扫描仪的精度为0.03mm；
S2、构建鲟鱼鱼体的外形曲线已经确定鲟鱼鱼体的长度M：如图2所示，建立坐标系，以步骤S1中获取的鲟鱼模型吻突尖端作为坐标原点，以鲟鱼模型的吻突尖端到鱼体以及鱼尾连接处的中心点之间的直线为X轴，根据步骤S1获取的三维鱼体模型为基础构建二维的鲟鱼鱼体外形曲线，其外形曲线包括鲟鱼鱼体的背部曲线和鲟鱼鱼体的腹部曲线；鲟鱼模型的吻突尖端到尾部尖端的直线投影在X轴上的长度即为鲟鱼鱼体长度M；
S3、外形曲线的处理：以步骤S2建立的坐标系为基础，将获取的鲟鱼鱼体外形曲线沿X轴均匀等分k份，在X轴上获取包括原点在内的k+1个横坐标，鲟鱼鱼体的背部曲线以及鲟鱼鱼体的腹部曲线上共获取2(k+1)个坐标点，鲟鱼鱼体的背部曲线坐标点定义为(x s,f u(x s))，鲟鱼鱼体的腹部曲线坐标点定义为(x s,f l(x s))；对获取的坐标点进行无量纲处理，得到无量纲坐标点，鲟鱼鱼体的背部曲线无量纲坐标定义为(x s,f’ u(x s))，鲟鱼鱼体的腹部曲线无量纲坐标点定义为(x s,f’ l(x s))，无量纲坐标点之间依次连接并进行光滑处理后获取光滑的鲟鱼鱼体外形曲线；无量纲处理中变量之间的关系定义如下：
Figure PCTCN2019101758-appb-000010
式中，t代表X轴上的坐标点，u为鲟鱼鱼体的背部曲线，l为鲟鱼鱼体的腹部曲线，x t为鲟鱼鱼体的背部曲线以及鱼体的腹部曲线上坐标点的横坐标，M为鱼体长度；f u(x t)为横坐标为x t处鲟鱼鱼体的背部曲线上的纵坐标，f l(x t)为横坐标为x t处鲟鱼鱼体的腹部曲线上的纵坐标；f’ u(x t)为横坐标为x t处鲟鱼鱼体的背部曲线上的无量纲纵坐标，f’ l(x t)为横坐标为x t处鲟鱼鱼体的腹部曲线上的无量纲纵坐标；M为鲟鱼鱼体的长度。
由于在步骤S1中为了降低扫描的误差对构建鲟鱼模型准确性的影响，选取m只鲟鱼进行扫描，且每只鲟鱼扫描n次，因此，步骤S2中共获取m×n条鲟鱼鱼体外形曲线，步骤S3中每一条鲟鱼鱼体外形曲线上都能获取2(k+1)个坐标点，对坐标点进行无量纲处理，得到 无量纲坐标点，对获取的无量纲坐标点采用最小二乘法进行数据拟合，拟合后形成一条鲟鱼鱼体外形曲线，并且鲟鱼鱼体外形曲线趋向光滑，具体的拟合方式如下：
f(x)＝b 0+b 1x，其中：
Figure PCTCN2019101758-appb-000011
Figure PCTCN2019101758-appb-000012
式中：
Figure PCTCN2019101758-appb-000013
由于选取m只鲟鱼进行扫描，且每只鲟鱼扫描n次，共获取m×n组数据，因此，j取值为m×n；
式中：b 0与b 1为常数；
当对鲟鱼鱼体的背部曲线进行拟时，x i为X轴上的横坐标，f(x i)分别代表横坐标为x i时位于鲟鱼鱼体的背部曲线的纵坐标；
Figure PCTCN2019101758-appb-000014
为获取m×n组数据中横坐标x i的平均值；
Figure PCTCN2019101758-appb-000015
为横坐标为x i时鲟鱼鱼体的背部曲线上的纵坐标的平均值；
Figure PCTCN2019101758-appb-000016
为横坐标x i中i取值从1到j时所有横坐标的平均值，
Figure PCTCN2019101758-appb-000017
为横坐标为
Figure PCTCN2019101758-appb-000018
时位于鲟鱼鱼体的背部曲线上纵坐标；
当对鲟鱼鱼体的腹部曲线进行拟时，x i为X轴上的横坐标，f(x i)分别代表横坐标为x i时位于鲟鱼鱼体的腹部曲线的纵坐标；
Figure PCTCN2019101758-appb-000019
为获取m×n组数据中横坐标x i的平均值；
Figure PCTCN2019101758-appb-000020
为横坐标为x i时鲟鱼鱼体的腹部曲线上的纵坐标的平均值；
Figure PCTCN2019101758-appb-000021
为横坐标x i中i取值从1到j时所有横坐标的平均值，
Figure PCTCN2019101758-appb-000022
为横坐标为
Figure PCTCN2019101758-appb-000023
时位于鲟鱼鱼体的腹部曲线上纵坐标；
优选地，步骤S1中选取3只鲟鱼进行扫描，且每只鲟鱼扫描3次，共获取9组数据，上述式中，j取值为9；
S4、数据修正：根据步骤S3处理后得到光滑的鲟鱼鱼体外形曲线进行数据修正，包括头部数据修正、鱼鳍数据修正和尾部数据修正；数据修正后得到仿生翼型的外形曲线，仿生翼型的外形曲线包括仿生翼型的背部曲线和仿生翼型的腹部曲线，根据仿生翼型的外形曲线确定仿生翼型的最大厚度δ max；
上述步骤中，头部数据修正的具体步骤如下：
以791翼型为基础，以791翼型前缘为坐标原点，791翼型的前缘与后缘之间的直线为X轴，构建791翼型的外形曲线，791翼型的前缘与791翼型的外形曲线上任意一点之间的直线投影在X轴上的长度为x d’，791翼型的弦长为C；
鲟鱼鱼体的吻突尖端与鲟鱼鱼体外形曲线上任意一点的直线投影在X轴上的长度x d与鲟鱼鱼体长度M的比为x d/M，x d/M＞0.2部分的鲟鱼鱼体外形曲线上的坐标点数据不变，对x d/M≤0.2部分的鲟鱼鱼体外形曲线上的坐标点数据进行修正：将791翼型的外形曲线上x d’/C≤0.2的坐标点数据分别替换鲟鱼鱼体外形曲线上x d/M≤0.2的坐标点数据；791翼型的外形曲线与鲟鱼鱼体外形曲线的连接处采用圆弧法均匀过度。
鱼鳍数据修正的具体步骤如下：
鱼鳍数据修正包括背鳍数据修正和腹鳍数据修正；
腹鳍数据修正：鲟鱼鱼体的腹部曲线与鲟鱼鱼体腹部鱼鳍的外形曲线相交产生两个交点，分别为交点A和交点B；定义鲟鱼鱼体吻突尖端到交点A之间的直线投影在X轴上的长度为x q，鲟鱼鱼体吻突尖端到交点B之间的直线投影在X轴上的长度为x h，鲟鱼鱼体吻突尖端到鲟鱼鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a；鲟鱼鱼体的腹部曲线上x q/M≤x a/M≤x h/M部分采用圆弧法并结合鲟鱼鱼体的腹部曲线变化趋势进行光滑处理；
背鳍数据修正：鲟鱼鱼体的背部曲线与鲟鱼鱼体背部鱼鳍的外形曲线相交产生两个交点，分别为交点C和交点D；定义鲟鱼鱼体吻突尖端到交点C之间的直线投影在X轴上的长度为x q’，鲟鱼鱼体吻突尖端到交点D之间的直线投影在X轴上的长度为x h’，鲟鱼鱼体吻突尖端到鲟鱼鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a’；鲟鱼鱼体的背部曲线上x q’/M≤x a’/M≤x h’/M部分采用圆弧法并结合鲟鱼鱼体的背部曲线变化趋势进行光滑处理；
鱼尾数据修正的具体步骤如下：
鲟鱼鱼体吻突尖端到鲟鱼鱼体外形曲线任何一点的直线在X轴上投影的长度为x d，其中鲟鱼鱼体外形曲线上x d/M＜0.7部分的数据不变，x d/M≥0.7部分的数据按照鲟鱼鱼体的背部曲线以及鲟鱼鱼体的腹部曲线的流线方向向后延伸，鲟鱼鱼体的背部曲线以及鲟鱼鱼体的腹部曲线在鱼尾一侧产生一个交点，对交点处进行圆角处理。
S5、以步骤S2的坐标系为基础，将获取仿生翼型的外形曲线均匀等分a份，在X轴上获取包括原点在内的a+1个横坐标，仿生翼型的背部曲线以及仿生翼型的腹部曲线上共获取2(a+1)个坐标点，根据获取的坐标点以及步骤S4中获取的最大厚度δ max计算控制点坐标；
所述控制点坐标包括仿生翼型背部曲线控制点坐标(x d,|f u(x d)|)和仿生翼型腹部曲线控制点坐标(x d,|f l(x d)|)，其计算公式如下：
|f l(x d)|＝f l(x i)/δ max，|f u(x d)|＝f u(x i)/δ max
式中：f u(x i)为x i点处翼型背部曲线上的纵坐标，fl(x i)为x i点处翼型腹部曲线上的纵坐标，|f l(x d)|为仿生翼型腹部曲线上的控制点纵坐标，|f u(x d)|为仿生翼型背部曲线上的控制点纵坐标，δ max为仿生翼型的最大厚度。
优选地，a＝k，其中，当a取值为20，控制点坐标如表1所示；
表1拟合的仿生翼型叶片控制点坐标
Figure PCTCN2019101758-appb-000024
S6、仿生翼型叶片的建立：根据设计要求确定仿生翼型叶片的最大厚度，根据最大厚度以及表1中的控制点坐标计算仿生翼型叶片背部曲线上的坐标点以及仿生翼型叶片腹部曲线上的坐标点，将上述计算后得到的坐标点导入到三维设计软件中进行放样处理，生成仿生翼型叶片。
通过上述方法制备的鲟鱼仿生翼型叶片和NACA0012翼型以及NACA0015翼型在不同雷诺数的流体中进行试验，比较其升力系数、阻力系数以及其压力差，比较结果如图3-12所示。
其中Sturgeon hydrofoil代表鲟鱼仿生翼型叶片。
1、升力系数比较
图3-5表示分别在雷诺数Re＝1E6、3E6和5E6的流体中鲟鱼仿生翼型叶片、NACA0012翼型以及NACA0015翼型的升力系数，结果表明：在雷诺数Re＝1E6、3E6和5E6的流体中，鲟鱼翼型叶片的升力系数随着失速攻角的增大相应增大，鲟鱼翼型叶片在达到失速攻角前，升力系数均大于NACA0012翼型和NACA0015翼型；
2、阻力系数比较
图6-8表示分别在雷诺数Re＝1E6、3E6和5E6的流体中鲟鱼翼型叶片、NACA0012翼型以及NACA0015翼型的阻力系数，结果表明：在雷诺数Re＝1E6、3E6和5E6的流体中，鲟 鱼翼型叶片的阻力系数随着失速攻角的增大相应增大，鲟鱼翼型叶片在达到失速攻角前，阻力系数均小于NACA0012翼型和NACA0015翼型；
通过上述三种雷诺数的结果中发现，雷诺数越大，失速攻角越大，且最大升力系数也会相应增大；鲟鱼翼型叶片在达到失速攻角前，升力系数均大于NACA0012翼型和NACA0015翼型，而阻力系数却小于NACA0012翼型及NACA0015翼型，具有较好升阻特性。
3、压力差比较
图9-12表示分别在攻角5°，10°，15°和20°，雷诺数Re＝3E6处的三种翼型的中间横截面和翼型的交线处的压力分布，结果表明：NACA0012翼型和NACA0015翼型在同一块区域具有类似的趋势即随着攻角增加，上下翼面的压力差增大，从而产生更大的升力；鲟鱼翼型叶片比NACA0012翼型和NACA0015翼型在攻角5°，10°和15°时产生更大的升力，特别是在最大厚度区域，但是该区域也有可能会导致空化的产生；由于攻角20°大于鲟鱼翼型在雷诺数Re＝3E6条件下的失速攻角，鲟鱼翼型的失速攻角前文可查，上下翼面的压差突然减小；
上述结果表明，鲟鱼翼型叶片在达到失速迎角前具有比NACA0012翼型和NACA0015翼型更好的水力特性。
以上内容是结合具体实施方式对本发明作进一步详细说明，不能认定本发明具体实施只局限于这些说明，对于本发明所属技术领域的普通技术人员来说，在不脱离本发明的构思的前提下，还可以做出若干简单的推演或替换，都应当视为属于本发明所提交的权利要求书确定的保护范围。

Claims (10)

  1. 一种仿生翼型叶片，其特征在于，其外形曲线包括仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线；
    所述仿生翼型叶片的几何参数如下：
    α＝14.43°；
    β＝6.42°；
    式中，α为仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线在前缘形成的夹角；
    β为仿生翼型叶片背部曲线以及仿生翼型叶片腹部曲线在后缘形成的夹角。
  2. 根据权利要求1所述的一种仿生翼型叶片，其特征在于，所述仿生翼型叶片的设计方法包括以下步骤：
    S1、点云数据的获取：对鱼体进行扫描获取三维数字模型，即鱼体的点云数据，将鱼体的点云数据导入到逆向工程软件中获取三维鱼体模型；
    S2、构建鱼体外形曲线以及确定鱼体长度M：建立坐标系，以鱼体吻突尖端作为坐标原点，以鱼体吻突尖端到鱼体以及鱼尾连接处的中心点之间的直线为X轴，根据步骤S1获取的三维鱼体模型为基础构建二维的鱼体外形曲线，其外形曲线包括鱼体的背部曲线和鱼体的腹部曲线；鱼体模型的吻突尖端到尾部尖端的直线投影在X轴上的长度即为鱼体长度M；
    S3、外形曲线的处理：以步骤S2建立的坐标系为基础，将获取的鱼体外形曲线沿X轴均匀等分k份，在X轴上获取包括原点在内的k+1个横坐标，鱼体的背部曲线以及鱼体的腹部曲线上共获取2(k+1)个坐标点，对获取的坐标点进行无量纲处理，得到无量纲坐标点，无量纲坐标点之间依次连接并进行光滑处理后获取光滑的鱼体外形曲线；
    S4、数据修正：根据步骤S3处理后得到光滑的鱼体外形曲线进行数据修正，包括头部数据修正、鱼鳍数据修正和尾部数据修正；数据修正后得到仿生翼型的外形曲线，仿生翼型的外形曲线包括仿生翼型的背部曲线和仿生翼型的腹部曲线，根据仿生翼型的外形曲线确定仿生翼型的最大厚度δ max；
    S5、以步骤S2的坐标系为基础，将仿生翼型的外形曲线均匀等分a份，在X轴上获取包括原点在内的a+1个横坐标，仿生翼型的背部曲线以及仿生翼型的腹部曲线上共获取2(a+1)个坐标点，根据获取的坐标点以及步骤S4中获取的最大厚度δ max计算控制点坐标；
    S6、仿生翼型叶片的建立：根据设计要求确定仿生翼型叶片的最大厚度，根据最大厚度以及控制点坐标计算仿生翼型叶片背部曲线上的坐标点以及仿生翼型叶片腹部曲线上的坐标点，将上述计算后得到的坐标点导入到三维设计软件中进行放样处理，生成仿生翼型叶片。
  3. 根据权利要求2所述的一种仿生翼型叶片，其特征在于，所述步骤S4中头部数据修 正的具体步骤如下：
    以791翼型为基础，以791翼型前缘为坐标原点，791翼型的前缘与后缘之间的直线为X轴，构建791翼型的外形曲线，791翼型的前缘与791翼型的外形曲线上任意一点之间的直线投影在X轴上的长度为x d’，791翼型的弦长为C；
    鱼体的吻突尖端与鱼体外形曲线上任意一点的直线投影在X轴上的长度x d与鱼体长度M的比为x d/M，x d/M＞0.2部分的鱼体外形曲线上的坐标点数据不变，对x d/M≤0.2部分的鱼体外形曲线上的坐标点数据进行修正：将791翼型的外形曲线上x d’/C≤0.2的坐标点数据分别替换鱼体外形曲线上x d/M≤0.2的坐标点数据；791翼型的外形曲线与鱼体外形曲线的连接处采用圆弧法均匀过度。
  4. 根据权利要求2所述的一种仿生翼型叶片，其特征在于，所述步骤S4中鱼鳍数据修正的具体步骤如下：
    腹鳍数据修正：鱼体的腹部曲线与鱼体腹部鱼鳍的外形曲线相交产生两个交点，分别为交点A和交点B；定义鱼体吻突尖端到交点A之间的直线投影在X轴上的长度为x q，鱼体吻突尖端到交点B之间的直线投影在X轴上的长度为x h，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a；鱼体的腹部曲线上x q/M≤x a/M≤x h/M部分采用圆弧法并结合鱼体的腹部曲线变化趋势进行光滑处理；
    背鳍数据修正：鱼体的背部曲线与鱼体背部鱼鳍的外形曲线相交产生两个交点，分别为交点C和交点D；定义鱼体吻突尖端到交点C之间的直线投影在X轴上的长度为x q’，鱼体吻突尖端到交点D之间的直线投影在X轴上的长度为x h’，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a’；鱼体的背部曲线上x q’/M≤x a’/M≤x h’/M部分采用圆弧法并结合鱼体的背部曲线变化趋势进行光滑处理。
  5. 根据权利要求2所述的一种仿生翼型叶片，其特征在于，所述步骤S4中尾部数据修正的具体步骤如下：
    鱼头吻突尖端到鱼体外形曲线任何一点的直线在X轴上投影的长度为x d，其中鱼体外形曲线上x d/M＜0.7部分的数据不变，x d/M≥0.7部分的数据按照鱼体的背部曲线以及鱼体的腹部曲线的流线方向向后延伸，鱼体的背部曲线以及鱼体的腹部曲线在鱼尾一侧产生一个交点，对交点处进行圆角处理。
  6. 根据权利要求2所述的一种仿生翼型叶片，其特征在于，所述步骤S4中数据修正的具体步骤如下：
    头部数据修正：以791翼型为基础，以791翼型前缘为坐标原点，791翼型的前缘与后缘之间的直线为X轴，构建791翼型的外形曲线，791翼型的前缘与791翼型的外形曲线上 任意一点之间的直线投影在X轴上的长度为x d’，791翼型的弦长为C；
    鱼体的吻突尖端与鱼体外形曲线上任意一点的直线投影在X轴上的长度x d与鱼体长度M的比为x d/M，x d/M＞0.2部分的鱼体外形曲线上的坐标点数据不变，对x d/M≤0.2部分的鱼体外形曲线上的坐标点数据进行修正：将791翼型的外形曲线上x d’/C≤0.2的的坐标点数据分别替换鱼体外形曲线上x d/M≤0.2的坐标点数据；791翼型的外形曲线与鱼体外形曲线的连接处采用圆弧法均匀过度；
    鱼鳍数据修正，包括背鳍数据修正和腹鳍数据修正；
    腹鳍数据修正：鱼体的腹部曲线与鱼体腹部鱼鳍的外形曲线相交产生两个交点，分别为交点A和交点B；定义鱼体吻突尖端到交点A之间的直线投影在X轴上的长度为x q，鱼体吻突尖端到交点B之间的直线投影在X轴上的长度的x h，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a；鱼体的腹部曲线上x q/M≤x a/M≤x h/M部分采用圆弧法并结合鱼体的腹部曲线变化趋势进行光滑处理；
    背鳍数据修正：鱼体的背部曲线与鱼体背部鱼鳍的外形曲线相交产生两个交点，分别为交点C和交点D；定义鱼体吻突尖端到交点C之间的直线投影在X轴上的长度为x q’，鱼体吻突尖端到交点D之间的直线投影在X轴上的长度的x h’，鱼体吻突尖端到鱼体的腹部曲线上任意一点的直线投影在X轴上的长度为x a’；鱼体的背部曲线上x q’/M≤x a’/M≤x h’/M部分采用圆弧法并结合鱼体的背部曲线变化趋势进行光滑处理；
    尾部数据修正：鱼头吻突尖端到鱼体外形曲线任何一点的直线在X轴上投影的长度为x d，其中鱼体外形曲线上x d/M＜0.7部分的数据不变，x d/M≥0.7部分的数据按照鱼体的背部曲线以及鱼体的腹部曲线的流线方向向后延伸，鱼体的背部曲线以及鱼体的腹部曲线在鱼尾一侧产生一个交点，对交点处进行圆角处理。
  7. 根据权利要求2所述的一种仿生翼型叶片，其特征在于，所述步骤S3中对鱼体背部曲线以及鱼体的腹部曲线上的坐标点进行无量纲处理，鱼体的背部曲线坐标点定义为(x t,f u(x t))，鱼体的腹部曲线坐标点定义为(x t,f l(x t))；背部曲线无量纲坐标定义为(x t,f’ u(x t))，腹部曲线无量纲坐标定义为(x t,f’ l(x t))，无量纲处理中变量之间的关系定义如下：
    Figure PCTCN2019101758-appb-100001
    式中，t代表X轴上的坐标点，u为鱼体的背部曲线，l为鱼体的腹部曲线，x t为鱼体的背部曲线以及鱼体的腹部曲线上坐标点的横坐标，M为鱼体长度；f u(x t)为横坐标为x t处鱼体的背部曲线上的纵坐标，f l(x t)为横坐标为x t处鱼体的腹部曲线上的纵坐标；f’ u(x t)为横坐标为x t处鱼体的背部曲线上的无量纲纵坐标，f’ l(x t)为横坐标为x t处鱼体的腹部曲线上的无量纲纵 坐标。
  8. 根据权利要求2所述的一种仿生翼型叶片，其特征在于，所述步骤S5中计算控制点坐标的公式如下：
    |f l(x d)|＝f l(x i)/δ max，|f u(x d)|＝f u(x i)/δ max
    式中：f u(x i)为x i点处翼型背部曲线上的纵坐标，fl(x i)为x i点处翼型腹部曲线上的纵坐标，|f l(x d)|为仿生翼型腹部曲线上的控制点纵坐标，|f u(x d)|为仿生翼型背部曲线上的控制点纵坐标，δ max为仿生翼型的最大厚度。
  9. 根据权利要求2-8任一项所述的一种仿生翼型叶片，其特征在于，所述步骤S1采用m只鱼体进行扫描，且每只鱼体扫描n次，共获取m×n组数据，共获取m×n条鱼体外形曲线，对m×n条鱼体外形曲线进行S3步骤处理获取无量纲坐标，对无量纲坐标进行数据拟合，获取一条光滑的鱼体外形曲线。
  10. 根据权利要求9所述的一种仿生翼型叶片，其特征在于，所述的数据拟合采用最小二乘法进行拟合，具体的拟合方式如下：
    f(x)＝b 0+b 1x
    其中：
    Figure PCTCN2019101758-appb-100002
    Figure PCTCN2019101758-appb-100003
    式中：
    Figure PCTCN2019101758-appb-100004
    由于选取m只鱼体进行扫描，且每只鱼体扫描n次，共获取m×n组数据，因此，j取值为m×n；式中：b 0与b 1为常数；
    x i为X轴上的横坐标，f(x i)分别代表横坐标为x i时位于鱼体的背部曲线或鱼体的腹部曲线上的纵坐标；
    Figure PCTCN2019101758-appb-100005
    为获取m×n组数据中横坐标x i的平均值；
    Figure PCTCN2019101758-appb-100006
    为横坐标为x i时分别位于鱼体的背部曲线或者鱼体的腹部曲线上的纵坐标的平均值；
    Figure PCTCN2019101758-appb-100007
    为横坐标x i中i取值从1到j时所有横坐标的平均值，
    Figure PCTCN2019101758-appb-100008
    为横坐标为
    Figure PCTCN2019101758-appb-100009
    时位于鱼体的背部曲线上或鱼体的腹部曲线上的纵坐标。
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Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN114857053A (zh) * 2022-05-30 2022-08-05 杭州老板电器股份有限公司 一种蜗壳、多翼离心风机以及油烟机

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116050028B (zh) * 2023-03-30 2023-06-20 陕西空天信息技术有限公司 叶轮叶片确定方法、计算机可读存储介质和电子设备

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1303990A (zh) * 2000-01-12 2001-07-18 三菱重工业株式会社 透平机动叶片
CN103147909A (zh) * 2013-03-07 2013-06-12 毛建华 升力型椭圆球式真空磁悬浮风力机
CN104653395A (zh) * 2015-01-19 2015-05-27 河南科技大学 鱼摆尾型升阻融合垂直轴风轮
CN104729822A (zh) * 2015-01-16 2015-06-24 中国民航大学 一种涡轮叶片尾迹模拟装置
CN108386383A (zh) * 2018-02-24 2018-08-10 西安交通大学 一种结合鲹科鱼体和鸟翼的交叉仿生叶片及其制备方法

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102163244A (zh) * 2010-12-30 2011-08-24 北京理工大学 一种叶片前缘豚头型处理方法
CN102032213B (zh) * 2010-12-30 2012-09-26 北京理工大学 一种端区叶片前缘仿生处理方法
CN105201728B (zh) * 2015-09-28 2017-12-15 中国海洋大学 一种水平轴潮流能水轮机组合翼型叶片的设计方法
US10858088B2 (en) * 2016-08-31 2020-12-08 David E. Shormann Biomimetic airfoil bodies and methods of designing and making same
CN108518295A (zh) * 2018-03-28 2018-09-11 中国海洋大学 潮流能水轮机叶片层流翼型设计方法

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN1303990A (zh) * 2000-01-12 2001-07-18 三菱重工业株式会社 透平机动叶片
CN103147909A (zh) * 2013-03-07 2013-06-12 毛建华 升力型椭圆球式真空磁悬浮风力机
CN104729822A (zh) * 2015-01-16 2015-06-24 中国民航大学 一种涡轮叶片尾迹模拟装置
CN104653395A (zh) * 2015-01-19 2015-05-27 河南科技大学 鱼摆尾型升阻融合垂直轴风轮
CN108386383A (zh) * 2018-02-24 2018-08-10 西安交通大学 一种结合鲹科鱼体和鸟翼的交叉仿生叶片及其制备方法

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CN114857053A (zh) * 2022-05-30 2022-08-05 杭州老板电器股份有限公司 一种蜗壳、多翼离心风机以及油烟机
CN114857053B (zh) * 2022-05-30 2024-02-27 杭州老板电器股份有限公司 一种蜗壳、多翼离心风机以及油烟机

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