EA201500723A1 - METHOD OF DESIGNING A THREE-DIMENSIONAL CURVED AERODYNAMIC PROFILE - Google Patents
METHOD OF DESIGNING A THREE-DIMENSIONAL CURVED AERODYNAMIC PROFILEInfo
- Publication number
- EA201500723A1 EA201500723A1 EA201500723A EA201500723A EA201500723A1 EA 201500723 A1 EA201500723 A1 EA 201500723A1 EA 201500723 A EA201500723 A EA 201500723A EA 201500723 A EA201500723 A EA 201500723A EA 201500723 A1 EA201500723 A1 EA 201500723A1
- Authority
- EA
- Eurasian Patent Office
- Prior art keywords
- aerodynamic profile
- section
- dimensional
- profile
- cross
- Prior art date
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C3/00—Wings
- B64C3/10—Shape of wings
- B64C3/14—Aerofoil profile
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
- B64C11/16—Blades
- B64C11/18—Aerodynamic features
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C27/00—Rotorcraft; Rotors peculiar thereto
- B64C27/32—Rotors
- B64C27/46—Blades
- B64C27/467—Aerodynamic features
-
- 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
- Y02T50/00—Aeronautics or air transport
- Y02T50/10—Drag reduction
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Mechanical Engineering (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Wind Motors (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
Способ проектирования сечения трёхмерного изогнутого профиля аэродинамической поверхности. Данный способ включает в себя следующие шаги: сбор данных координат дуги сечения стандартного двухмерного аэродинамического профиля, таких как (x, у) и (х, у); в соответствии с данными координат сечения стандартного аэродинамического профиля, вычисление приращения между точками координат по оси х хорды; определение радиуса вращения R сечения аэродинамического профиля согласно проекту; создание координат дуги (х, y, z) сечения трёхмерного аэродинамического профиля, где у- значение координаты по толщине двухмерного профиля; и по аналогии - вычисление группы координат (х, у, z) дуги сечения трёхмерного аэродинамического профиля и т.д. Данный способ улучшает аэродинамический профиль лопасти путем оптимизации сечения трёхмерного изогнутого аэродинамического профиля, и соответствующего увеличения эффективности аэродинамической силы лопасти несущего винта, изготовленной из тех же материалов и имеющей те же структурные характеристики.A method for designing a cross section of a three-dimensional curved profile of an aerodynamic surface. This method includes the following steps: collecting coordinate data of the arc section of a standard two-dimensional aerodynamic profile, such as (x, y) and (x, y); in accordance with the coordinate data of the section of the standard aerodynamic profile, calculating the increment between the coordinate points along the x axis of the chord; determination of the radius of rotation R of the cross section of the aerodynamic profile according to the project; creation of the coordinates of the arc (x, y, z) of the cross section of the three-dimensional aerodynamic profile, where y is the coordinate value along the thickness of the two-dimensional profile; and by analogy - the calculation of the group of coordinates (x, y, z) of the cross-sectional arc of a three-dimensional aerodynamic profile, etc. This method improves the aerodynamic profile of the blade by optimizing the cross-section of a three-dimensional curved aerodynamic profile, and a corresponding increase in the efficiency of the aerodynamic force of the rotor blade made of the same materials and having the same structural characteristics.
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201310053925.8A CN103967718B (en) | 2013-02-05 | 2013-02-05 | The method for designing of three-dimension curved surface aerofoil profile |
PCT/CN2013/074018 WO2014121554A1 (en) | 2013-02-05 | 2013-04-10 | Design method for three-dimensional curved airfoil section |
Publications (2)
Publication Number | Publication Date |
---|---|
EA201500723A1 true EA201500723A1 (en) | 2015-12-30 |
EA029645B1 EA029645B1 (en) | 2018-04-30 |
Family
ID=51237627
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EA201500723A EA029645B1 (en) | 2013-02-05 | 2013-04-10 | Design method for three-dimensional curved airfoil section |
Country Status (3)
Country | Link |
---|---|
CN (1) | CN103967718B (en) |
EA (1) | EA029645B1 (en) |
WO (1) | WO2014121554A1 (en) |
Families Citing this family (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN104881510B (en) * | 2015-02-13 | 2018-06-05 | 南京航空航天大学 | A kind of lifting airscrew/tail-rotor aerodynamic interference numerical value emulation method |
CN108100195B (en) * | 2016-11-25 | 2019-09-17 | 成都天府新区光启未来技术研究院 | Method and apparatus for Design of Propeller |
CN109229417B (en) * | 2018-08-06 | 2020-08-21 | 浙江工业大学 | Bionic combined wing section design method based on wing carving |
CN109185009B (en) * | 2018-09-07 | 2020-05-08 | 杭州江河水电科技有限公司 | Passive self-adaptive reciprocating bidirectional water flow impeller device |
RU2769545C1 (en) * | 2021-05-14 | 2022-04-04 | Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") | Aerodynamic profile of the lifting element of the aircraft |
CN113970311A (en) * | 2021-10-12 | 2022-01-25 | 中国航空工业集团公司北京长城计量测试技术研究所 | Aero-engine blade vector approximation iterative measurement method |
CN115544667B (en) * | 2022-10-31 | 2024-05-10 | 南京航空航天大学 | Equivalent disk method based on phyllanthus momentum source coupling CFD |
CN117313235A (en) * | 2023-09-23 | 2023-12-29 | 哈尔滨工业大学 | Special unmanned aerial vehicle optimized wing blade design method based on machine learning |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3625459A (en) * | 1970-05-18 | 1971-12-07 | Walter C Brown | Airfoil design |
US7941300B1 (en) * | 2008-02-29 | 2011-05-10 | Florida Turbine Technologies, Inc. | Process for the design of an airfoil |
CN101968821B (en) * | 2009-07-28 | 2013-05-01 | 联合船舶设计发展中心 | Airfoil profile design method and structure applicable for multi-speed domain |
CN101923584B (en) * | 2009-10-30 | 2012-08-15 | 重庆大学 | Method for designing special wind turbine airfoil profile and special wind turbine airfoil profile |
CN102235325B (en) * | 2011-07-01 | 2012-10-31 | 重庆大学 | Method for designing airfoil section of blade tip of wind machine based on airfoil section integration and mixed trailing edge modification |
-
2013
- 2013-02-05 CN CN201310053925.8A patent/CN103967718B/en not_active Expired - Fee Related
- 2013-04-10 WO PCT/CN2013/074018 patent/WO2014121554A1/en active Application Filing
- 2013-04-10 EA EA201500723A patent/EA029645B1/en unknown
Also Published As
Publication number | Publication date |
---|---|
EA029645B1 (en) | 2018-04-30 |
WO2014121554A1 (en) | 2014-08-14 |
CN103967718A (en) | 2014-08-06 |
CN103967718B (en) | 2016-10-05 |
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