CN109726462A - A kind of angle of attack method for quickly identifying suitable for aerofoil profile - Google Patents
A kind of angle of attack method for quickly identifying suitable for aerofoil profile Download PDFInfo
- Publication number
- CN109726462A CN109726462A CN201811579375.2A CN201811579375A CN109726462A CN 109726462 A CN109726462 A CN 109726462A CN 201811579375 A CN201811579375 A CN 201811579375A CN 109726462 A CN109726462 A CN 109726462A
- Authority
- CN
- China
- Prior art keywords
- aerofoil profile
- angle
- attack
- pixel
- edge pixel
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
Classifications
-
- 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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Abstract
A kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, belongs to hydrodynamic calculations technical field.The present invention is the following steps are included: obtain flow field picture by high-speed camera, binarization of gray value processing is carried out to the flow field picture and obtains gray scale picture, the gray scale picture is established into coordinate system, and the coordinate of each pixel and gray value in the gray scale picture are established into data matrix；Leading edge pixel and trailing edge pixel in the gray scale picture are identified according to aerofoil profile leading edge and trailing edge decision criteria, and the leading edge pixel and trailing edge pixel are denoted as A (x respectively1,y1)、B(x2,y2)；The aerofoil profile angle of attack is calculated according to the coordinate of the leading edge pixel and the trailing edge pixel.The flow analysis in hydrodynamics field and structure is instructed to design using the aerofoil profile angle of attack parameter that above-mentioned steps recognize.The present invention can reduce aerofoil profile angle of attack identification workload, improve aerofoil profile angle of attack accuracy of identification.
Description
Technical field
The present invention relates to a kind of angle of attack method for quickly identifying suitable for aerofoil profile, belong to hydrodynamic calculations technical field.
Background technique
In aerospace field, in order to avoid flutter and resonance in power stall, structure, the dynamic characteristic of Oscillating Airfoil by
Pay attention to more and more.In hydraulic research, the additional forces of generation and the disturbance of sound component are rotated to rapids
Stream process, the development in boundary layer, fluidal texture spatial and temporal distributions have important influence, the flow field phase of nonrotational/rotatable parts
The physical mechanism mutually interfered is always the key points and difficulties studied.In propeller, turbine pump, hydraulic turbine start and stop, fly ease, increase and decrease
In the transient processes such as load, transient process transient flow can make the effective angle of attack of lifting surface change, and internal flow is complicated
It is changeable, show strong unstability.Therefore, understand the change of object unstable state hydrodynamic load and vibration under dynamic change
Change, to hydraulic transient process Unsteady Flow Mechanism and dynamic characteristics is understood, the design of Optimum Hydraulic machinery improves waterpower
Performance has great significance.
Basic unit of the hydrofoil as structure of hydraulic machinery studies often by as basic moving boundaries circumferential motion problem
Object.Experimental study is the basic methods for seeking physical mechanism, and wherein high-speed fluid visualization is widely used in fluid
It tests in measuring study.The working principle of high-speed fluid visualization mainly claps flow phenomenon using high speed camera
It takes the photograph, and carries out qualitative and quantitative analysis for shooting picture.The research work flowed around hydrofoil is based on mostly before this
It is carried out under stationary body, i.e. the angle of attack of aerofoil profile is fixed and invariable；However the high speed whole flow field streamed for moving boundaries is shown
There is the hydrofoil angle of attack moment the variation the problem of, in order to analyze under dynamic change non-stable diffusion and hydrodynamic load
Variation, the determination of the hydrofoil angle of attack is highly important.However accurately identify that there has been no mature skills for the hydrofoil angle of attack at present
Art method, mostly using manually carrying out rough measurement method to picture, heavy workload and error is also larger；Therefore the present invention mentions
A kind of angle of attack method for quickly identifying suitable for aerofoil profile is gone out.
Summary of the invention
In order to solve the problems, such as the prior art, there are the aerofoil profile angles of attack to identify that heavy workload, precision are inaccurate, and the present invention is public
A kind of angle of attack method for quickly identifying technical problems to be solved suitable for aerofoil profile opened are as follows: reduce the aerofoil profile angle of attack and identify work
Amount improves aerofoil profile angle of attack accuracy of identification.
Object of the present invention is to what is be achieved through the following technical solutions.
A kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, comprising the following steps: by taking the photograph at a high speed
Camera obtains flow field picture, carries out binarization of gray value processing to the flow field picture and obtains gray scale picture, by the gray scale picture
Coordinate system is established, and the coordinate of each pixel and gray value in the gray scale picture are established into data matrix；Before aerofoil profile
Edge and trailing edge decision criteria identify leading edge pixel and trailing edge pixel in the gray scale picture, by the leading edge pixel
And trailing edge pixel is denoted as A (x respectively1,y1)、B (x2,y2)；According to the leading edge pixel and the trailing edge pixel
Coordinate calculate the aerofoil profile angle of attack, the aerofoil profile angle of attack is denoted as α.
A kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, further includes following steps: application is above-mentioned
The aerofoil profile angle of attack parameter of step identification instructs the flow analysis in hydrodynamics field and structure to design.
According to the aerofoil profile angle of attack parameter that above-mentioned steps recognize, the variation range of the aerofoil profile angle of attack can be obtained, is further looked at
Corresponding Airfoil Flow structure under each angle of attack, analyzes whether dynamic characteristics suffered by aerofoil profile meets technical requirements, can instruct
The optimization design of engineering structure.In addition, obtained aerofoil profile angle of attack parameter can also be the health monitoring under dynamic change, structure failure
Diagnosis, the application of structural vibration control etc. provide strong support, are with a wide range of applications and benefit.
Preferentially, in order to promote the contrast of gray value, background color is preset as corresponding grey scale and is worth small color, it is described
Aerofoil profile color presets in the picture of flow field are the big color of corresponding grey scale value.The gray value little finger of toe gray threshold is 140, gray scale
Value refers to greatly gray threshold 210, the optimal gray value differences range of contrast effect: 70~200.
Further preferably, the background face of the flow field picture is preset as kermesinus, and corresponding grey scale value is 130, the stream
Aerofoil profile color in field picture is glassy yellow, corresponding grey scale value 215.
Preferentially, the threshold value of the binary conversion treatment of the flow field picture is 150~200.
Preferentially, the decision criteria of the leading edge pixel and the trailing edge pixel is that pixel gray value is
255, the smallest pixel of X-coordinate value is the leading edge pixel, and the maximum pixel of X-coordinate value is the trailing edge pixel.
Further preferably, aerofoil profile decision criteria is
Y=1E-6x5-0.0001x4+0.0044x3-0.0861x2+0.8206x+0.2172,(x>0)；
Y=6E-8x6-7E-6x5+0.0003x4-0.0074x3+0.0863x2-0.4422x-0.3151,(x<0)。
If pixel coordinate (x, y) meets above-mentioned formula, for the boundary of aerofoil profile.
Preferentially, the aerofoil profile angle of attack calculation formula is α=β * arctan ((y2-y1)/(x2-x1)), β repairs for pixel
Positive coefficient.
Further preferably, the pixel correction factor value range is 0.95~1.
The utility model has the advantages that
1, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, obtains flow field by high-speed camera
Picture carries out gray proces, identifies hydrofoil leading edge pixel and trailing edge pixel and then realizes the quick calculating of the aerofoil profile angle of attack,
Working efficiency can be significantly improved and attack angle measurement precision is high.
2, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, obtains flow field by high-speed camera
Picture carries out gray proces, and background color is preset as corresponding grey scale and is worth small color, the aerofoil profile color presets in the picture of flow field
For the big color of corresponding grey scale value.Gray value little finger of toe gray threshold is 140, the big finger gray threshold 210 of gray value, contrast effect
Optimal gray value differences range is 70~200；Intensity contrast effect can be significantly improved.
3, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, at experiment conclusion and theory
Reason provides aerofoil profile and determines formula, on the basis of determining leading edge, trailing edge, further determines aerofoil profile, improves and determine efficiency.
4, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, at experiment conclusion and theory
Reason provides the angle of attack and quickly calculates correction formula, improves accuracy of identification.
5, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, is obtained by remote high-speed camera
Take flow field picture, do not influence experimentation, suitable for various moving boundaries stream aerofoil profile angle measurement experiment.
6, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention, the aerofoil profile recognized using above-mentioned steps
Angle of attack parameter can obtain the variation range of the aerofoil profile angle of attack, further look at the corresponding Airfoil Flow structure under each angle of attack, point
Whether dynamic characteristics suffered by analysis aerofoil profile meets technical requirements, can instruct the optimization design of engineering structure.In addition, the obtained wing
Type angle of attack parameter can also mention for health monitoring, structure failure diagnosis, the application of structural vibration control etc. under dynamic change
For strong support, it is with a wide range of applications and benefit.
Detailed description of the invention
Fig. 1 is a kind of flow chart of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention；
Fig. 2 be a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention aerofoil profile leading edge pixel and
Trailing edge pixel determines the flow chart of identification；
Fig. 3 is a kind of aerofoil profile angle of attack Computing Principle of angle of attack method for quickly identifying suitable for aerofoil profile disclosed by the invention
Figure.
Specific embodiment
With reference to the accompanying drawing, a specific embodiment of the invention is illustrated.
Embodiment 1
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed in this implementation, passes through height
Fast video camera obtains flow field picture, and convection current field picture carries out binarization of gray value processing and obtains gray scale picture, gray scale picture is established
Coordinate system, and the coordinate of pixel each in gray scale picture and gray value are established into data matrix；According to aerofoil profile leading edge and trailing edge
Decision criteria identifies leading edge pixel and trailing edge pixel in the gray scale picture, by leading edge pixel and trailing edge pixel
Point is denoted as A (x respectively1,y1)、B(x2,y2)；Aerofoil profile is calculated according to the coordinate of leading edge pixel and the trailing edge pixel to attack
Angle, the aerofoil profile angle of attack are denoted as α.The background face of flow field picture is preset as kermesinus, and corresponding grey scale value is 130, in the picture of flow field
Aerofoil profile color is glassy yellow, corresponding grey scale value 215.
The threshold value of the binary conversion treatment of flow field picture is 150~200.
As shown in Fig. 2, it is that 255, X is sat that the decision criteria of leading edge pixel and trailing edge pixel, which is pixel gray value,
The smallest pixel of scale value is leading edge pixel, and the maximum pixel of X-coordinate value is trailing edge pixel.
As shown in figure 3, aerofoil profile decision criteria is
Y=1E-6x5-0.0001x4+0.0044x3-0.0861x2+0.8206x+0.2172,(x>0)；
Y=6E-8x6-7E-6x5+0.0003x4-0.0074x3+0.0863x2-0.4422x-0.3151,(x<0)。
Aerofoil profile angle of attack calculation formula is α=β * arctan ((y2-y1)/(x2-x1)), β is pixel correction factor, pixel
Point correction factor value range is 0.95~1.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of angle of attack method for quickly identifying suitable for aerofoil profile disclosed in this implementation first will
Flow field background brushing is kermesinus, and corresponding grey scale value is 130, and aerofoil profile brushing is glassy yellow, then corresponding grey scale value 215 passes through
High-speed camera obtains flow field picture；Convection current field picture progress binarization of gray value processing acquisition gray scale picture, the two of flow field picture
The threshold value of value processing is taken as 160；Then coordinate system XOY established to gray scale picture, and by pixel each in gray scale picture
Coordinate and gray value establish data matrix；Since aerofoil profile color is glassy yellow, then all white of gray scale picture wing centre section type, i.e., grey
Angle value is 255；Then under conditions of guaranteeing gray value is 255, the smallest pixel of X-coordinate value is leading edge pixel A (x1,y1),
The maximum pixel of X coordinate value is trailing edge pixel B (x2,y2).Before connection, trailing edge pixel A (x1,y1)、B(x2,y2) be
The chord length of aerofoil profile；The angle of attack of aerofoil profile is defined as the angle of aerofoil profile chord length and direction of flow, and direction of flow is X-direction；Therefore according to preceding
Trailing edge pixel A (x1,y1)、B(x2,y2) coordinate value can calculate the angle of attack of aerofoil profile, aerofoil profile angle of attack calculation formula is α=β *
arctan((y2-y1)/(x2-x1)), wherein pixel correction factor value 0.98.
Further, coordinate system is established using leading edge pixel A as origin, the boundary of aerofoil profile is identified according to aerofoil profile decision criteria,
Its aerofoil profile decision criteria is
Y=1E-6x5-0.0001x4+0.0044x3-0.0861x2+0.8206x+0.2172,(x>0)；
Y=6E-8x6-7E-6x5+0.0003x4-0.0074x3+0.0863x2-0.4422x-0.3151,(x<0)。
If pixel coordinate meets above-mentioned formula, for the boundary of aerofoil profile.
The flow analysis in hydrodynamics field can be instructed to set with structure using the aerofoil profile angle of attack parameter that above-mentioned steps recognize
Meter.
According to the aerofoil profile angle of attack parameter that above-mentioned steps recognize, the variation range of the aerofoil profile angle of attack can be obtained, is further looked at
Corresponding Airfoil Flow structure under each angle of attack, analyzes whether dynamic characteristics suffered by aerofoil profile meets technical requirements, can instruct
The optimization design of engineering structure.In addition, obtained aerofoil profile angle of attack parameter can also be the health monitoring under dynamic change, structure failure
Diagnosis, the application of structural vibration control etc. provide strong support, are with a wide range of applications and benefit.
Above-described specific descriptions have carried out further specifically the purpose of invention, technical scheme and beneficial effects
It is bright, it should be understood that the above is only a specific embodiment of the present invention, the protection model being not intended to limit the present invention
It encloses, all within the spirits and principles of the present invention, any modification, equivalent substitution, improvement and etc. done should be included in the present invention
Protection scope within.
Claims (10)
1. a kind of angle of attack method for quickly identifying suitable for aerofoil profile, it is characterised in that: the following steps are included: passing through high-speed camera
Flow field picture is obtained, binarization of gray value processing is carried out to the flow field picture and obtains gray scale picture, the gray scale picture is established
Coordinate system, and the coordinate of each pixel and gray value in the gray scale picture are established into data matrix；According to aerofoil profile leading edge with
Trailing edge decision criteria identifies leading edge pixel and trailing edge pixel in the gray scale picture, by the leading edge pixel and
Trailing edge pixel is denoted as A (x respectively1,y1)、B(x2,y2)；According to the leading edge pixel and the coordinate of the trailing edge pixel
The aerofoil profile angle of attack is calculated, the aerofoil profile angle of attack is denoted as α.
2. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as described in claim 1, it is characterised in that: further include as follows
Step instructs the flow analysis in hydrodynamics field and structure to design using the aerofoil profile angle of attack parameter that above-mentioned steps recognize.
3. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 2, it is characterised in that: according to above-mentioned step
Suddenly the aerofoil profile angle of attack parameter recognized, can obtain the variation range of the aerofoil profile angle of attack, further look at the corresponding wing under each angle of attack
Type flow field structure, analyzes whether dynamic characteristics suffered by aerofoil profile meets technical requirements, can instruct the optimization design of engineering structure；
In addition, obtained aerofoil profile angle of attack parameter can also be health monitoring, structure failure diagnosis, the structural vibration control etc. under dynamic change
The application of aspect provides strong support, is with a wide range of applications and benefit.
4. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 1 or 2, it is characterised in that: by background
Color presets are that corresponding grey scale is worth small color, and the aerofoil profile color presets in the flow field picture are the big face of corresponding grey scale value
Color；The gray value little finger of toe gray threshold is 140, the big finger gray threshold 210 of gray value, the optimal gray value differences of contrast effect
Range: 70~200.
5. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 4, it is characterised in that: the flow field figure
The background face of piece is preset as kermesinus, and corresponding grey scale value is 130, and the aerofoil profile color in the flow field picture is glassy yellow, right
Answer gray value 215.
6. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 1 or 2, it is characterised in that: the stream
The threshold value of the binary conversion treatment of field picture is 150~200.
7. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 1 or 2, it is characterised in that: before described
The decision criteria of edge pixel and the trailing edge pixel is that pixel gray value is 255, and the smallest pixel of X-coordinate value is
The leading edge pixel, the maximum pixel of X-coordinate value are the trailing edge pixel.
8. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 7, it is characterised in that: aerofoil profile determines quasi-
Then it is
Y=1E-6x5-0.0001x4+0.0044x3-0.0861x2+0.8206x+0.2172,(x>0)；
Y=6E-8x6-7E-6x5+0.0003x4-0.0074x3+0.0863x2-0.4422x-0.3151,(x<0)；
If pixel coordinate (x, y) meets above-mentioned formula, for the boundary of aerofoil profile.
9. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 8, it is characterised in that: the aerofoil profile is attacked
Angle calculation formula is α=β * arctan ((y2-y1)/(x2-x1)), β is pixel correction factor.
10. a kind of angle of attack method for quickly identifying suitable for aerofoil profile as claimed in claim 9, it is characterised in that: the pixel
Point correction factor value range is 0.95~1.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811579375.2A CN109726462B (en) | 2018-12-24 | 2018-12-24 | Attack angle quick identification method suitable for wing profile |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811579375.2A CN109726462B (en) | 2018-12-24 | 2018-12-24 | Attack angle quick identification method suitable for wing profile |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109726462A true CN109726462A (en) | 2019-05-07 |
| CN109726462B CN109726462B (en) | 2021-05-04 |
Family
ID=66297102
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811579375.2A Active CN109726462B (en) | 2018-12-24 | 2018-12-24 | Attack angle quick identification method suitable for wing profile |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109726462B (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009102739A2 (en) * | 2008-02-13 | 2009-08-20 | Bell Helicopter Textron Inc. | Rotorcraft with variable incident wing |
| CN102052266A (en) * | 2010-12-29 | 2011-05-11 | 南京航空航天大学 | After-load blunt trailing edge wing profile designed based on sharp trailing edge wing profile |
| EP2633447A2 (en) * | 2010-10-29 | 2013-09-04 | The Boeing Company | Method and system to account for angle of attack effects in engine noise shielding tests for airplanes |
| CN103293333A (en) * | 2013-05-10 | 2013-09-11 | 东南大学 | Two-dimensional flow velocity field measurement method and device of interlaced scanning CCD (charge coupled device) |
| CN105351248A (en) * | 2015-12-17 | 2016-02-24 | 新昌县三新空调风机有限公司 | High-performance airfoil for fan |
| CN106050739A (en) * | 2016-07-22 | 2016-10-26 | 西安航空制动科技有限公司 | High-performance wing section for cooling fan |
| CN107818197A (en) * | 2017-09-15 | 2018-03-20 | 南京航空航天大学 | A kind of force measuring method and device of the supersonic profile based on PIV technologies |
-
2018
- 2018-12-24 CN CN201811579375.2A patent/CN109726462B/en active Active
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2009102739A2 (en) * | 2008-02-13 | 2009-08-20 | Bell Helicopter Textron Inc. | Rotorcraft with variable incident wing |
| EP2633447A2 (en) * | 2010-10-29 | 2013-09-04 | The Boeing Company | Method and system to account for angle of attack effects in engine noise shielding tests for airplanes |
| CN102052266A (en) * | 2010-12-29 | 2011-05-11 | 南京航空航天大学 | After-load blunt trailing edge wing profile designed based on sharp trailing edge wing profile |
| CN103293333A (en) * | 2013-05-10 | 2013-09-11 | 东南大学 | Two-dimensional flow velocity field measurement method and device of interlaced scanning CCD (charge coupled device) |
| CN105351248A (en) * | 2015-12-17 | 2016-02-24 | 新昌县三新空调风机有限公司 | High-performance airfoil for fan |
| CN106050739A (en) * | 2016-07-22 | 2016-10-26 | 西安航空制动科技有限公司 | High-performance wing section for cooling fan |
| CN107818197A (en) * | 2017-09-15 | 2018-03-20 | 南京航空航天大学 | A kind of force measuring method and device of the supersonic profile based on PIV technologies |
Non-Patent Citations (6)
| Title |
|---|
| MENGJIE ZHANG等: "《Lagrangian-based numerical investigation of aerodynamic performance of an oscillating foil》", 《SPRINGER》 * |
| 张孟杰等: "《绕振荡水翼空化流动实验与数值研究》", 《第二十九届全国水动力学研讨会论文集（上册）》 * |
| 张效慈等: "《两维翼水动力振动和流场显示的粒子图像测速实验》", 《中国造船》 * |
| 曹洪才: "《任意运动变形边界流场测量PIV算法的研究》", 《中国优秀硕士学位论文全文数据库 信息科技辑》 * |
| 王献孚: "《船用翼理论》", 31 October 1998 * |
| 赵婕著: "《图像特征提取与语义分析》", 31 July 2015 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN109726462B (en) | 2021-05-04 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109460566B (en) | Aerodynamic robust optimization design method for thick airfoil section on inner side of wind turbine blade | |
| Aranake et al. | Computational analysis of shrouded wind turbine configurations using a 3-dimensional RANS solver | |
| Dou et al. | Experimental investigation of the performance and wake effect of a small-scale wind turbine in a wind tunnel | |
| CN109459582A (en) | Laser particle image speed measurement data processing method based on moving boundary self-identifying | |
| Tescione et al. | Analysis of a free vortex wake model for the study of the rotor and near wake flow of a vertical axis wind turbine | |
| Han et al. | LES method of the tip clearance vortex cavitation in a propelling pump with special emphasis on the cavitation-vortex interaction | |
| CN106919731B (en) | Method for determining wake flow of wind turbine generator for different wind direction angles | |
| CN108533451A (en) | A kind of pitch control method of wind power generating set | |
| Tian et al. | Bionic design of wind turbine blade based on long-eared owl’s airfoil | |
| Lua et al. | Effects of pitching phase angle and amplitude on a two-dimensional flapping wing in hovering mode | |
| Uşar et al. | Cavitation simulation on horizontal axis marine current turbines | |
| Feng et al. | Research on aerodynamic characteristics of straight-bladed vertical axis wind turbine with S series airfoils | |
| CN109726462A (en) | A kind of angle of attack method for quickly identifying suitable for aerofoil profile | |
| CN110110444B (en) | Large-scale commercial ship-oriented coupling type wing sail optimization method and system | |
| Xu et al. | Accuracy of the aerodynamic performance of wind turbines using vortex core models in the free vortex wake method | |
| CN115434877B (en) | Blade internal state detection method and device | |
| Li et al. | Effects of offset blade on aerodynamic characteristics of small-scale vertical axis wind turbine | |
| Xiong et al. | Wind direction and speed forecasting optimization algorithm for ship based on time series and Kalman filter | |
| CN113408077B (en) | Sawtooth-shaped hydrofoil leading edge optimization method based on proxy model | |
| Hou et al. | Hydrodynamic performance analysis of propeller-rudder system with the rudder parameters changing | |
| Li et al. | Experimental and numerical investigation of the influence of roughness and turbulence on LUT airfoil performance | |
| CN112926132B (en) | Fixed wing airfoil aerodynamic shape design method considering influence of three-dimensional effect | |
| CN203770019U (en) | 100-W wind turbine blade | |
| Sun et al. | Analysis of influencing factors on lift coefficients of autonomous sailboat double sail propulsion system based on vortex panel method | |
| CN112283051A (en) | Vibration signal characteristic optimization method and system based on lift line model |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |