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Design method of three-dimensional curved airfoil

A technology of three-dimensional curved surface and design method, which is applied in the direction of rotorcraft, mechanical equipment, wing shape, etc., can solve the problem that the geometric envelope of the two-dimensional plane airfoil is not like translation, and achieve the effect of improving the efficiency of aerodynamic force extraction

Inactive Publication Date: 2016-10-05
XINJIANG SHANGFU NEW ENERGY TECH
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AI Technical Summary

Problems solved by technology

[0012] Because the airfoil envelope is planar, when the two-dimensional plane airfoil rotates, its sweep trajectory will form a torus in the rotation plane. Like translation, in the case of rotation, it will not be able to achieve full-pass mechanical wrapping effect with the incoming Euler streamline

Method used

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  • Design method of three-dimensional curved airfoil
  • Design method of three-dimensional curved airfoil
  • Design method of three-dimensional curved airfoil

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Embodiment Construction

[0038] The following table is the three-dimensional coordinate values ​​of the three-dimensional curved surface airfoil of the present invention on the rotating cylinder (R=10.26m), which is a specific embodiment of the present invention. The first three sets of data in each line are the three-dimensional coordinates of the upper arc; the last three sets of data in each line are the three-dimensional coordinates of the lower arc.

[0039]

[0040] Concrete steps of the present invention are described as:

[0041] f) Extract any conventional 2-D airfoil upper arc (or lower arc) coordinate data (x 1 ,y 1 ), (x 2 ,y 2 )…

[0042] g) According to the conventional airfoil coordinate data, calculate the increment ΔL between each x-coordinate point of the chord line 1 , ΔL 2 ,…ΔL i (ΔL 1 =X i+1 -X i )

[0043] h) Determine the radius of rotation (position) R of the airfoil (including the rotor and the rotating blade) to be arranged according to the design

[0044] i) cho...

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Abstract

Disclosed is a design method for a three-dimensional curved airfoil section. The method comprises the following steps: collecting arc coordinate data of a conventional 2D airfoil section such as (x1, y1) and (x2, y2); according to the conventional airfoil section coordinate data, calculating an increment such as &Dgr;L1 and &Dgr;L2 between each x coordinate point of a chord; determining a radius of rotation R of the airfoil section to be arranged according to the design; selecting x1=z1=0.707R, where y1=0; inserting x1, z1, &Dgr;L1 and R into a specific formula to calculate x2 and z2, thereby creating a three-dimensional airfoil section arc coordinate (x2, y2, z2), wherein y2 is still a coordinate value of the thickness of the 2D airfoil section; and by this analogy, calculating a three-dimensional airfoil section arc coordinate cluster (x3, y3, z3), etc. This method improves the aerodynamic profile of a blade by means of optimising a three-dimensional curved airfoil section, thereby increasing aerodynamic force efficiency of a rotary blade on the basis of the same materials and structural arrangement.

Description

technical field [0001] The present invention relates to a design method of a three-dimensional curved surface airfoil, which is not only aimed at renewable energy wind power generator blades, but also can be aimed at various types of aircraft with rotary wings, jet engines, steam / gas turbines and super large water turbine blades, etc. It can be used as the basic geometric unit to construct various wings, rotors and blades. Background technique [0002] The helicopter is a vertical take-off and landing aircraft with the rotor as its main source of lift. Its vertical take-off and landing, air hovering and other performances depend to a large extent on the aerodynamic characteristics of the rotor, which is different from the aerodynamic shape of the rotor blades. have a very close relationship. Therefore, the rotor airfoil, which is the basic element of the aerodynamic shape of the rotor blade, has an important influence on the flow field and aerodynamic characteristics of the...

Claims

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Application Information

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IPC IPC(8): F03D80/00F03B3/12F01D5/12B64C27/467
CPCB64C3/14B64C11/18B64C27/467Y02T50/10
Inventor 陈宇奇
Owner XINJIANG SHANGFU NEW ENERGY TECH
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