CN106777590A - A kind of air-foil matches method for designing - Google Patents

A kind of air-foil matches method for designing Download PDF

Info

Publication number
CN106777590A
CN106777590A CN201611090349.4A CN201611090349A CN106777590A CN 106777590 A CN106777590 A CN 106777590A CN 201611090349 A CN201611090349 A CN 201611090349A CN 106777590 A CN106777590 A CN 106777590A
Authority
CN
China
Prior art keywords
coefficient
wing
lift
parameter
angle
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.)
Pending
Application number
CN201611090349.4A
Other languages
Chinese (zh)
Inventor
詹光
胡婕
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Original Assignee
Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC filed Critical Shenyang Aircraft Design and Research Institute Aviation Industry of China AVIC
Priority to CN201611090349.4A priority Critical patent/CN106777590A/en
Publication of CN106777590A publication Critical patent/CN106777590A/en
Pending legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F30/00—Computer-aided design [CAD]
    • G06F30/10—Geometric CAD
    • G06F30/15—Vehicle, aircraft or watercraft design
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06N—COMPUTING ARRANGEMENTS BASED ON SPECIFIC COMPUTATIONAL MODELS
    • G06N3/00—Computing arrangements based on biological models
    • G06N3/12—Computing arrangements based on biological models using genetic models
    • G06N3/126—Evolutionary algorithms, e.g. genetic algorithms or genetic programming
    • G—PHYSICS
    • G06—COMPUTING; CALCULATING OR COUNTING
    • G06F—ELECTRIC DIGITAL DATA PROCESSING
    • G06F2111/00—Details relating to CAD techniques
    • G06F2111/10—Numerical modelling
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Theoretical Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Biophysics (AREA)
  • Geometry (AREA)
  • General Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Bioinformatics & Cheminformatics (AREA)
  • Bioinformatics & Computational Biology (AREA)
  • Evolutionary Biology (AREA)
  • Evolutionary Computation (AREA)
  • General Engineering & Computer Science (AREA)
  • Molecular Biology (AREA)
  • Genetics & Genomics (AREA)
  • General Health & Medical Sciences (AREA)
  • Computational Linguistics (AREA)
  • Computing Systems (AREA)
  • Biomedical Technology (AREA)
  • Artificial Intelligence (AREA)
  • Mathematical Physics (AREA)
  • Software Systems (AREA)
  • Data Mining & Analysis (AREA)
  • Automation & Control Theory (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physiology (AREA)
  • Computational Mathematics (AREA)
  • Mathematical Analysis (AREA)
  • Mathematical Optimization (AREA)
  • Pure & Applied Mathematics (AREA)
  • Computer Hardware Design (AREA)
  • Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The invention provides a kind of air-foil apolegamy method for designing, one group of wing parameter is selected first and this group of parametrization wing aerodynamic analysis model of wing parameter is set up, choose the first angle of attack α1With the second angle of attack α2, calculate α1Corresponding first lift coefficient CL1With the first moment coefficient CM1, calculate α2Corresponding second lift coefficient CL2With the second moment coefficient CM2；Then according to previously given CLDesign is calculated and CLIf corresponding 3rd angle of attack α3, CLLift coefficient corresponding with design point is set to, and calculates zero lift moment coefficient CM0；Calculate again and α3Corresponding resistance coefficient CD3, and to resistance coefficient CD3It is modified, and calculates the corresponding lift-drag ratio K of point of useMake；Enter row constraint and optimization to parameter finally by optimization problem is defined, obtain optimal wing parameter, obtain and design the maximum lift-drag ratio of Point matching by optimal wing parameter.

Description

A kind of air-foil matches method for designing
Technical field
The present invention relates to wing design technical field, more particularly to a kind of air-foil apolegamy method for designing.
Background technology
The universal air-foil apolegamy of industrial quarters is all first to be selected from wing storehouse according to lifting resistance characteristic, torque factor requirement Matching degree aerofoil profile higher, then to selecting the wing apolegamy aerofoil profile of plane geometry parameter and defining the aerofoil profiles such as several groups of geometric twists Relevant parameter, Aerodynamic characteristics are carried out to it, if Aerodynamic characteristics meet require if carry out next step optimization design, if It is unsatisfactory for then matching aerofoil profile to the wing for selecting plane geometry parameter again, re-defines the relevant parameter of the aerofoil profiles such as geometric twist simultaneously Aerodynamic characteristics are carried out to it, is required until Aerodynamic characteristics meet.
The design analysis of aerofoil profile, above method abbreviation 2D wing designs are concentrated on due to Main Analysis.Early stage dopey Aerofoil profile determine the Aerodynamic Characteristics of wing substantially, by the aerofoil profile of manual iteration match design can meet Development Schedule will Ask.But with the development that becomes more meticulous of pneumatic design technology, the continuous improvement of analysis means possesses low aspect ratio, big angle of sweep etc. The a large amount of of feature wing use, and aerofoil profile and full machine aerodynamic characteristic are simultaneously insufficient corresponding, to be found using original method and matched very much Aerofoil profile it is relatively difficult, and operating efficiency is relatively low.
Be to solve problem above, the research of more and more academias focuses on 3D wing designs, will wing it is whole as one Build face carries out the analysis and optimization of 3-dimensional.Obviously, this method is to simulation capacity, data-handling capacity and optimization method etc. Various aspects requirement is higher, is not appropriate in the larger aircraft concept of Parameters variation, concept phase, especially in wing The design point offset problem that produces during aerofoil profile apolegamy design, although obtain maximum lift-drag ratio, but with the lift coefficient of point of use Corresponding lift-drag ratio is but not necessarily maximum lift-drag ratio.
The content of the invention
It is at least one defect for overcoming above-mentioned prior art to exist, is designed the invention provides a kind of apolegamy of air-foil Method, comprises the following steps：
Step one, selectes one group of wing parameter { X0, X1, X2, X3...1, and set up this group of parametrization wing of wing parameter Aerodynamic analysis model, chooses the first angle of attack α1With the second angle of attack α2, calculate α1Corresponding first lift coefficient CL1With the first torque system Number CM1, calculate α2Corresponding second lift coefficient CL2With the second moment coefficient CM2；
Step 2, is set according to previously given CL and is calculated and C by formula (1)LIf corresponding 3rd angle of attack α3, CL is set to Lift coefficient corresponding with design point,
α3=α1+(CLIf-CL1)/(CL2-CL1)*(α2-α1) (1)；
Zero lift moment coefficient C is calculated according to formula (2)M0,
CM0=CM1–(CM2–CM1)/(CL2-CL1)*CL1(2)；
Step 3, calculates and α3Corresponding resistance coefficient CD3, and to resistance coefficient CD3It is modified, and by formula (3) Calculating the corresponding lift-drag ratio K of point of use makes, wherein δCDIt is viscous drag correction coefficient,
K makes=CLIf/(CD3+δCD) (3)；
Step 4, defines constraints and optimization aim, and the optimization aim is K is made maximization, by the constraint bar Part and optimization aim substitute into genetic algorithm and calculate, and obtain optimal wing parameter { X0, X1, X2, X3... optimal, by optimal wing ginseng Number { X0, X1, X2, X3... most preferably as the wing parameter in step one, a step one is re-executed to step 3, trying to achieve makes Made with the maximum lift-drag ratio K of pointmax。
Preferably, the wing parameter selected in step one includes the main occupy-place torsion angle of wing and aerofoil profile parameter.
Preferably, the first angle of attack α in step 21It is 2 °, the second angle of attack α2It is 4 °, CLIf value is 0.2.
Preferably, the constraints in step 4 includes the constraints of variable ranges of wing parameter and the model of zero lift moment coefficient Enclose constraint.
Preferably, the genetic algorithm in step 4 uses archipelago genetic algorithm.
A kind of air-foil apolegamy method for designing that the present invention is provided, under conditions of wing planform parameter determination, The maximum lift-drag ratio matched with design point is quickly found out by calculating, and can guarantee that the maximum lift-drag ratio meets constraints, Solve design point offset problem present in design.
Brief description of the drawings
Fig. 1 is the point of use schematic diagram that the air-foil that the present invention is provided matches method for designing.
Specific embodiment
To make the purpose, technical scheme and advantage of present invention implementation clearer, below in conjunction with the embodiment of the present invention Accompanying drawing, the technical scheme in the embodiment of the present invention is further described in more detail.In the accompanying drawings, identical from start to finish or class As label represent same or similar element or the element with same or like function.Described embodiment is the present invention A part of embodiment, rather than whole embodiments.Embodiment below with reference to Description of Drawings is exemplary, it is intended to used It is of the invention in explaining, and be not considered as limiting the invention.Based on the embodiment in the present invention, ordinary skill people The every other embodiment that member is obtained under the premise of creative work is not made, belongs to the scope of protection of the invention.
Below by specific embodiment, the present invention is described in further detail.
Specific embodiment：
Step one, the Hicks-Henne methods of application enhancements are parameterized to basic aerofoil profile, from aerodynamic analysis software FLO22, sets up parametrization wing analysis Mathematical Modeling, and wing parameter includes the main occupy-place torsion angle of wing and aerofoil profile parameter { Yita [4], Airfoil_1 [23], Airfoil_2 [23], Airfoil_3 [23] ... ... }, selectes 2 ° of low incidence for first meets Angle α1, it is the first angle of attack α to select 4 ° of low incidence2, calculate α1Corresponding first lift coefficient CL1It is 0.15, the first moment coefficient CM1It is -0.015, calculates α2Corresponding second lift coefficient CL2It is 0.25, the second moment coefficient CM2For -0.03；
Step 2, previously given lift coefficient C corresponding with design pointL0.2 is set to, is calculated by formula below (1) Go out CLIf corresponding 3rd angle of attack α3It is 3 °,
α3=α1+(CLIf-CL1)/(CL2-CL1)*(α2-α1) (1)；
Zero lift moment coefficient C is calculated according to formula below (2)M0It is 0.0075,
CM0=CM1–(CM2–CM1)/(CL2-CL1)*CL1(2)；
Step 3, calculates and α3Corresponding resistance coefficient CD3It is 0.005, and to resistance coefficient CD3It is modified, and passes through Formula below (3) calculates the corresponding lift-drag ratio K of point of use to be made to be 20, wherein viscous drag correction coefficient δCDIt is 0.005,
K makes=CLIf/(CD3+δCD) (3)；
Step 4, analysis environments are optimized using ModelCenter software buildings, define constraints and optimization aim, institute The range constraint of constraints of variable ranges and zero lift moment coefficient of the constraints including wing parameter is stated, the optimization aim is to make K makes maximization, wherein：
Variable：{ Yita [4], Airfoil_1 [23], Airfoil_2 [23], Airfoil_3 [23] ... ... }；
Range of variables：-0.1<Airfoil_1[1]<0.1 ... ...
Constraint：CM0, Camber [3], Thinkness [3]；
Restriction range：0.006<CM0<0.008,0<Camber[1]<0.05 ... ...
Optimization aim：K makes maximization；
The constraints and optimization aim are substituted into archipelago genetic algorithm to calculate, one group of optimal wing parameter is obtained, will Optimal wing parameter re-executes a step one to step 3 as the wing parameter in step one, by formula (1) to public affairs The maximum lift-drag ratio K that formula (3) tries to achieve point of use makes max be 22.
The above, specific embodiment only of the invention, but protection scope of the present invention is not limited thereto, and it is any Those familiar with the art the invention discloses technical scope in, the change or replacement that can be readily occurred in, all should It is included within the scope of the present invention.Therefore, protection scope of the present invention should be with the scope of the claims It is accurate.

Claims (5)

1. a kind of air-foil matches method for designing, it is characterised in that comprise the following steps：
Step one, selectes one group of wing parameter { X0, X1, X2, X3...1, and set up this group of parametrization wing aerodynamic of wing parameter Analysis model, chooses the first angle of attack α1With the second angle of attack α2, calculate α1Corresponding first lift coefficient CL1With the first moment coefficient CM1, calculate α2Corresponding second lift coefficient CL2With the second moment coefficient CM2；
Step 2, according to previously given CL setsCalculated by formula (1) and CL setsCorresponding 3rd angle of attack α3, CL setsIt is and design point Corresponding lift coefficient,
α3=α1+(CL sets-CL1)/(CL2-CL1)*(α2-α1) (1)；
Zero lift moment coefficient C is calculated according to formula (2)M0,
CM0=CM1–(CM2–CM1)/(CL2-CL1)*CL1(2)；
Step 3, calculates and α3Corresponding resistance coefficient CD3, and to resistance coefficient CD3It is modified, and is calculated by formula (3) The corresponding lift-drag ratio K of point of use makes, wherein δCDIt is viscous drag correction coefficient,
KMake=CL sets/(CD3+δCD) (3)；
Step 4, defines constraints and optimization aim, the optimization aim to make K make maximization, by the constraints and Optimization aim substitutes into genetic algorithm and calculates, and obtains optimal wing parameter { X0, X1, X2, X3... optimal, by optimal wing parameter {X0, X1, X2, X3...Most preferablyAs the wing parameter in step one, a step one is re-executed to step 3, try to achieve point of use Maximum lift-drag ratio KMake max。
2. air-foil according to claim 1 matches method for designing, it is characterised in that the wing ginseng selected in step one Number includes the main occupy-place torsion angle of wing and aerofoil profile parameter.
3. air-foil according to claim 1 matches method for designing, it is characterised in that the first angle of attack α in step 21 It is 2 °, the second angle of attack α2It is 4 °, CL setsBe worth is 0.2.
4. air-foil according to claim 1 matches method for designing, it is characterised in that the constraints bag in step 4 Include the range constraint of the constraints of variable ranges and zero lift moment coefficient of wing parameter.
5. air-foil according to claim 1 matches method for designing, it is characterised in that the genetic algorithm in step 4 is adopted Use archipelago genetic algorithm.
CN201611090349.4A 2016-11-30 2016-11-30 A kind of air-foil matches method for designing Pending CN106777590A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN201611090349.4A CN106777590A (en) 2016-11-30 2016-11-30 A kind of air-foil matches method for designing

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN201611090349.4A CN106777590A (en) 2016-11-30 2016-11-30 A kind of air-foil matches method for designing

Publications (1)

Publication Number Publication Date
CN106777590A true CN106777590A (en) 2017-05-31

Family

ID=58913571

Family Applications (1)

Application Number Title Priority Date Filing Date
CN201611090349.4A Pending CN106777590A (en) 2016-11-30 2016-11-30 A kind of air-foil matches method for designing

Country Status (1)

Country Link
CN (1) CN106777590A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN110750839A (en) * 2019-08-26 2020-02-04 深圳市道通智能航空技术有限公司 Design method of propeller wing profile and terminal equipment
CN111291304A (en) * 2018-12-07 2020-06-16 波音公司 Flight control system for determining estimated dynamic pressure based on lift and drag coefficients

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102941925B (en) * 2012-11-05 2015-05-13 北京航空航天大学 Elastic correction method of airplane lifting resistance aerodynamic characteristics
CN106021808A (en) * 2016-06-07 2016-10-12 西北工业大学 Low span chord ratio aerofoil type designing method considering three-dimensional effect

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102941925B (en) * 2012-11-05 2015-05-13 北京航空航天大学 Elastic correction method of airplane lifting resistance aerodynamic characteristics
CN106021808A (en) * 2016-06-07 2016-10-12 西北工业大学 Low span chord ratio aerofoil type designing method considering three-dimensional effect

Non-Patent Citations (4)

* Cited by examiner, † Cited by third party
Title
ISMOYO HARYANTO等: "《Optimization Of Maximum Lift To Drag Ratio On Airfoil Design Based On Artificial Neural Network Utilizing Genetic Algorithm》", 《APPLIED MECHANICS AND MATERIALS》 *
商重阳等: "《飞机的性能、稳定性、动力学与控制》", 31 December 2013, 航空工业出版社 *
王晓鹏: "《遗传算法及其在气动优化设计中的应用研究》", 《中国优秀博硕士学位论文全文数据库（博士） 工程科技II辑》 *
王清等: "《基于遗传算法的旋翼翼型综合气动优化设计》", 《航空动力学报》 *

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111291304A (en) * 2018-12-07 2020-06-16 波音公司 Flight control system for determining estimated dynamic pressure based on lift and drag coefficients
CN111291304B (en) * 2018-12-07 2024-05-24 波音公司 Flight control system for determining estimated dynamic pressure based on lift and drag coefficients
CN110750839A (en) * 2019-08-26 2020-02-04 深圳市道通智能航空技术有限公司 Design method of propeller wing profile and terminal equipment

Similar Documents

Publication Publication Date Title
CN109460566B (en) Aerodynamic robust optimization design method for thick airfoil section on inner side of wind turbine blade
CN109409013B (en) Intelligent optimization design method for wind wheel of low-wind-speed wind turbine generator
CN109190283A (en) A kind of wind mill airfoil Aerodynamic optimization method considering high Turbulent Free incoming flow effect
CN103136422B (en) The integrated intermediate gauge Airfoil Design method be combined with B-spline of aerofoil profile
CN106126791B (en) A kind of hypersonic wing aerodynamic force/heat analysis method for considering geometrical uncertainty
CN109711048A (en) It is a kind of to consider pneumatic and structure polymorphic type design variable Wing design method
CN105183996A (en) Surface element correction and grid beforehand self-adaption calculation method
CN107330152B (en) Efficient pneumatic balancing method suitable for rotor craft
CN105046021B (en) The nonlinear optimization algorithm of unsteady aerodynamic force minimum state rational approximation
CN109343466B (en) Helical bevel gear shape cooperative machining parameter mixing back-adjustment correction method
CN104834772A (en) Artificial-neural-network-based inverse design method for aircraft airfoils/wings
CN107145677A (en) A kind of improved geometric parameter Airfoil Design method
CN106777590A (en) A kind of air-foil matches method for designing
CN104863799A (en) Method for designing wind turbine airfoil by using Bessel function curve
CN108038259B (en) Method for generating pneumatic component appearance based on curvature
Bottasso et al. Free-form design of rotor blades
Vasilopoulos et al. CAD-based aerodynamic optimization of a compressor stator using conventional and adjoint-driven approaches
CN103942366B (en) The aerofoil profile and its generation method of the continual curvature represented based on four sections of rational Béziercurves
CN107220415A (en) A kind of two-dimentional high lift device parameterization design method for meeting Engineering constraint based on nurbs curve
CN105353650B (en) Foundation temporarily rushes formula Asia across the super preset aperture model method of across the flow field pressure regulator valve in wind-tunnel Asia
CN105574221A (en) Improved CST (Class Function/Shape Function Transformation) airfoil profile parametric method
CN111859545B (en) Wide-speed-range high-lift-drag-ratio wing optimal design method considering lift matching
CN103043224B (en) Double-circle method for generating trailing edge flap control surface airfoil leading edge curve
Tong et al. Multi-objective aerodynamic optimization of supercritical wing with substantial pressure constraints
CN105260498B (en) A kind of large size civil aircraft wing variable camber design method

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
RJ01 Rejection of invention patent application after publication
RJ01 Rejection of invention patent application after publication

Application publication date: 20170531