CN109783858A - A method of optimize for low Reynolds number airfoil - Google Patents
A method of optimize for low Reynolds number airfoil Download PDFInfo
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Abstract
A method of optimize for low Reynolds number airfoil, according to mission requirements, CST function is compiled on Matlab software, aerofoil profile is parameterized with CST function, the parameter in CST function is inputted, obtains the geometric shape of the corresponding aerofoil profile of CST function, the geometric shape of aerofoil profile is imported into ICEM software, using the macro recording function of ICEM, complete to obtain grid file to the FEM meshing of aerofoil profile；Macro recording is carried out in Fluent software to be configured flight operating condition, Pneumatic Calculation condition, and grid file is imported into Fluent software, Pneumatic Calculation is completed, obtains wing section lift coefficient, lift resistance ratio；Wing section lift coefficient, the lift resistance ratio obtained to step (3) judges, if wing section lift coefficient, lift resistance ratio are all satisfied mission requirements, retains the corresponding CST function of geometric shape of aerofoil profile；Otherwise the parameter in CST function is adjusted；The high aerofoil profile of pneumatic efficiency has been obtained, the flying quality of aircraft is improved.
Description
Technical field
The present invention relates to a kind of methods for low Reynolds number airfoil optimization, belong near space vehicle field.
Background technique
The U.S. successively releases " predator ", the Global Hawk unmanned air vehicle in the nineties in last century, and paces are also closely followed in China, continuously
The models unmanned planes such as " rainbow ", " pterosaur " are developed, are fruitfully completed including a variety of military affairs such as strike, scouting and early warning
Task.From the point of view of current development trend, high-altitude, long endurance, multipurpose are the main direction of development of the following unmanned plane.
The cruising altitude of High Altitude UAV is located at stratosphere, and the region distance ground is generally in 20-30km, rarefaction of air,
Density is low, and kinematic viscosity coefficient is larger, therefore flight Reynolds number is compared with conventionally lower (Re ≈ 2 × 105), so promoting aircraft
Lift coefficient and lift resistance ratio when cruise are vital.
Under the conditions of current technology, the flying speed of Altitude Long Endurance Unmanned Air Vehicle is generally large, patrols if reduced by force
Speed of a ship or plane degree, aircraft have the danger of stall.
Summary of the invention
Present invention solves the technical problem that are as follows: it overcomes the shortage of prior art, provides a kind of for low Reynolds number airfoil optimization
Method, by aerofoil optimization, the cruising altitude for realizing High Altitude UAV is located at stratosphere, which generally exists
20-30km, rarefaction of air, density is low, in the biggish situation of kinematic viscosity coefficient, promotes the lift coefficient and liter when aircraft cruise
Ratio is hindered, realizes the cruise operation of High Altitude UAV.
The technical solution that the present invention solves are as follows: a method of optimize for low Reynolds number airfoil, steps are as follows:
(1) according to mission requirements, CST function is compiled on Matlab software, is parameterized aerofoil profile with CST function, input
Parameter in CST function obtains the geometric shape of the corresponding aerofoil profile of CST function；
(2) geometric shape of aerofoil profile is imported into ICEM software, using the macro recording function of ICEM, completes the finite element to aerofoil profile
Grid dividing obtains grid file；
(3) it carries out macro recording in Fluent software flight operating condition, Pneumatic Calculation are solved equation and be configured, by net
Lattice file imports Fluent software, completes Pneumatic Calculation, obtains lift coefficient, lift resistance ratio when aerofoil profile cruise；
(4) lift coefficient, lift resistance ratio judge when cruising the aerofoil profile that step (3) obtains, if lift when aerofoil profile is cruised
Coefficient, lift resistance ratio are all satisfied mission requirements, then retain the corresponding CST function of geometric shape of aerofoil profile in step (1)；Otherwise, it returns
Return the parameter in step (1) adjustment CST function.
Geometric shape, thickness, camber and leading-edge radius including aerofoil profile.
The CST function of compiling, including classification functionAnd shape functionTwo parts are multiplied to obtain CST function,
The curve of CST function representation is capable of the shape of accurate description low Reynolds number airfoil.
The parameter in CST function is inputted, specifically: in CST functionConstant, S after parameter input in part
Parameter in (ψ) can adjust.
Using the macro recording function of ICEM, the FEM meshing to aerofoil profile is completed, specifically: using full when grid dividing
Structured grid sets the far field front, top, lower section distance, rear distance, grid height of aerofoil profile.
Grid file is .mesh format.
Are solved by equation and is configured for flight operating condition, Pneumatic Calculation, specifically: the setting of flight operating condition includes: mission requirements
Flying height, flying speed, flight attitude；It includes simulation aerofoil profile Laminar Flow, transition prediction, rapids that Pneumatic Calculation, which solves equation,
The equation of flowing.
Pneumatic Calculation is completed, wing section lift coefficient, lift resistance ratio are obtained, specifically: using simulation aerofoil profile Laminar Flow, turn to twist
It predicts, the equation of turbulent flow, obtains lift coefficient, lift resistance ratio when aerofoil profile cruise.
When lift coefficient, lift resistance ratio judge when step (4) cruises to the aerofoil profile that step (3) obtains, mission requirements packet
The minimum value of cruise lift coefficient and the minimum value of lift resistance ratio are included, lift coefficient difference is big when the aerofoil profile that step (3) obtains is cruised
It is judged to meeting mission requirements in the minimum value of cruise lift coefficient and the minimum value of lift resistance ratio of mission requirements.
Step (4) return step (1) adjusts the parameter in CST function, specifically: it will be in CST functionPart
In parameter remain unchanged, adjustIn parameter.
The advantages of the present invention over the prior art are that:
(1) a kind of method for low Reynolds number airfoil optimization of the present invention, airfoil geometry modeling is simple, is conducive to optimize defeated
Enter the extraction of parameter；
(2) a kind of method for low Reynolds number airfoil optimization of the present invention makes full use of Fluid Mechanics Computation in optimization
Software is analyzed, computational solution precision is high, can be directly as the reference data of engineering design；
(3) a kind of method for low Reynolds number airfoil optimization of the present invention, optimization aim is clear, and iteration cycle is short, can contract
Casual labourer's journey lead time.
(4) present invention is innovative builds aerofoil profile modeling, grid dividing, Pneumatic Calculation on ISIGHT platform, according to
Optimization aim realizes the automatic selection of aerofoil profile.
(5) wing section lift coefficient and lift resistance ratio height that the present invention is gone out by optimization design, are conducive to the low of High Altitude UAV
Speed cruise, increases the airborne period of aircraft.
Detailed description of the invention
Fig. 1 is E387 aerofoil optimization flow diagram；
Fig. 2 is CST parametrization E387 aerofoil profile schematic diagram；
Fig. 3 is CST parametrization E387 aerofoil profile error schematic diagram；
Fig. 4 is ICEM grid division schematic diagram；
Fig. 5 is shape comparison diagram before and after aerofoil optimization；
Fig. 6 is lift coefficient comparison diagram before and after aerofoil optimization；
Fig. 7 is lift resistance ratio comparison diagram before and after aerofoil optimization.
Specific embodiment
The invention will be described in further detail in the following with reference to the drawings and specific embodiments.
It is E387 aerofoil profile that the present invention, which optimizes original aerofoil profile, which is typical low Reynolds number airfoil, and aerofoil profile main body is in preceding circle
The shape of metacone, maximum gauge are the 9% of chord length, and maximum camber is the 3.7% of chord length, and leading-edge radius is the 1.6% of chord length.
(1) according to mission requirements, CST function is compiled on Matlab software, is parameterized aerofoil profile with CST function, input
Parameter in CST function obtains the geometric shape of the corresponding aerofoil profile of CST function.
(2) geometric shape of aerofoil profile is imported into ICEM software, using the macro recording function of ICEM, completes the finite element to aerofoil profile
Grid dividing obtains grid file；
(3) it carries out macro recording in Fluent software flight operating condition, Pneumatic Calculation are solved equation and be configured, by net
Lattice file imports Fluent software, completes Pneumatic Calculation, obtains lift coefficient, lift resistance ratio when aerofoil profile cruise；
(4) lift coefficient, lift resistance ratio judge when cruising the aerofoil profile that step (3) obtains, if lift when aerofoil profile is cruised
Coefficient, lift resistance ratio are all satisfied mission requirements, then retain the corresponding CST function of geometric shape of aerofoil profile in step (1)；Otherwise, it returns
Return the parameter in step (1) adjustment CST function；
When parameterizing aerofoil profile, the geometric shape feature by CST function accurate description aerofoil profile, the thickness including aerofoil profile are needed
Degree, camber and leading-edge radius.The function includes classification functionWith shape function S (ψ), two parts are multiplied to obtain CST letter
Number, the curve of CST function representation are capable of the shape of accurate description low Reynolds number airfoil.Classification functionWherein, N1, N2 are the characteristic parameter of airfoil geometry shape classification function, preferably N1
It is 0.5, preferably N2 is 1, defines origin in the up-front front end of aerofoil profile, x-axis is directed toward aerofoil profile from the up-front front end of aerofoil profile
The center of trailing edge；, Ψ is aerofoil profile abscissa (coordinate that abscissa is denoted as x-axis),N preferably takes
4, B (i) be the parameter for controlling aerofoil profiles curvature, the parameter of aerofoil profiles curvature is controlled, with base profile (the i.e. E387 of optimization
Aerofoil profile) for, B (0) take 0.306, B (1) take 0.123, B (2) take 0.457B (2) take 0.277 (B3 trouble helps me to change, I
Here do not edit) and B (4) take 0.454,
For the n-order polynomial expansion of function, pass through the table of above formula
It states, can clearly understand the basic principle of CST parametrization dimensional airfoil.I=0,1,2 .., n；
In global optimization process design, the computational accuracy of each step in aerofoil profile calculating process should be considered, while wanting simultaneous
Calculating cycle is cared for, therefore, this patent realizes aerofoil profile parameter model, finite element analysis and ratio by building Automatic Optimal platform
To the function of screening, which can be rapidly completed iteration according to mission requirements, realize optimization aim.
As described in Figure 1, the present invention is preferably using E387 low Reynolds number airfoil as basic aerofoil profile, parametrization aerofoil profile and the original wing
The comparison diagram and Error Graph of type are as shown in Figure 2 and Figure 3, and Fig. 2 abscissa is the abscissa numerical value of aerofoil profile and the ratio of chord length, indulge and sit
It is designated as the Y value of aerofoil profile and the ratio of chord length, the abscissa of Fig. 3 is the abscissa numerical value of aerofoil profile and the ratio of chord length, always
Coordinate is CST Function Fitting error, and You Tuzhong data can see, and the aerofoil profile of CST method fitting is kissed substantially with former Curve of wing
It closes, error precision is controlled in 10-3 magnitude, meets engineering design needs；Second part is ICEM Auto--Generating Mesh module, such as
Shown in Fig. 4, full structured grid is used when grid dividing, far field front, top, lower section distance are 30 times of chord lengths, and rear distance is
40 times of chord lengths, first layer grid height are 10-5 times of chord length, and for y+ less than 1, which mainly completes the mapping of aerofoil profile point, line, surface
Task realizes the automatic function of dividing different airfoil profiles grid；Part III is that Fluent calculates macro recording, which mainly completes
The work of aerofoil profile aerodynamics evaluation will set flight operating condition when carrying out macro recording by taking this operating condition as an example, and flight attitude is to meet
Angle α=5 °, speed V=30m/s, height H=20km, restrain residual error err < 0.001, simulation aerofoil profile Laminar Flow, turn twist it is pre-
It surveys, the equation of turbulent flow selection Transition-SST equation, preferably equation is as follows:
Turn being preferably defined as the source item twisted
It destroys or laminar flow source item is defined as P againγ2=(2cγ1)ρΩγFturb；Eγ2=cγ2Pγ2γ；
Wherein: cγ1=0.03；cγ2=50；cγ3=0.5；σγ=1.0
FonsetTurn to twist for triggering, calculation method are as follows:
The boundary condition of γ equation is that wall surface normal direction flux is 0, become a mandarin locate normal direction flux be 1.
The equation can with accurate description aerofoil profile Laminar Flow, turbulent flow and turn twist position, later will be in calculated result
Lift coefficient and lift resistance ratio exported with text formatting, for subsequent result screening be ready；Part IV is that result was screened
Journey, the data calculated from upper step, and the result is compared with mission requirements, the mission requirements in this are
The lift coefficient of aerofoil profile is not less than 0.85 when 5 degree of angles of attack, and lift resistance ratio is not less than 60, and by lift coefficient and rises resistance on this basis
Than reaching maximum is set as optimization aim simultaneously, due to having met multiple-objection optimization requirement there are two optimization output variables, because
This carries out screening iteration using genetic algorithm, and specific method is that the CST different airfoil profiles parameterized are first divided into several populations, respectively
The calculated result of each population is analyzed, the difference of lift coefficient and lift resistance ratio and mission requirements is calculated, it is poor according to this
Value change input variable, iterates, the aerodynamic configuration after obtaining aerofoil profile final optimization pass.
Fig. 5 is aerodynamic configuration comparison diagram before and after aerofoil optimization, and abscissa is the abscissa numerical value of aerofoil profile and the ratio of chord length,
Ordinate is the Y value of aerofoil profile and the ratio of chord length, and as shown in table 1, the aerofoil profile leading edge after optimization is partly for major parameter variation
Diameter significantly increases before relatively optimizing, and the maximum gauge of aerofoil profile becomes smaller, and aerofoil profile lower surface is anti-recessed more obvious at rear position in,
I.e. the camber of aerofoil profile increases.
Parameter comparison before and after 1 aerofoil optimization of table
| Aerofoil profile | Thickness | Camber | Leading-edge radius |
| Original aerofoil profile | 9.1% | 3.7% | 1.6% |
| Optimize aerofoil profile | 9.4% | 4.9% | 1.9% |
Fig. 6 is lift coefficient comparison diagram before and after aerofoil optimization, and abscissa is flying angle, and ordinate is profile lift system
Number, Fig. 7 are lift resistance ratio comparison diagrams before and after aerofoil optimization, and abscissa is flying angle, and ordinate is aerofoil profile lift resistance ratio, in -3 °≤α
In < 9 ° of angle-of-attack range, the more original aerofoil profile of lift coefficient and lift resistance ratio of aerofoil profile has apparent increase after optimization.With 3 ° of angles of attack
For, the lift coefficient of aerofoil profile increases 10.8% after optimization, and lift resistance ratio improves 5.65%；In 8 ° of angles of attack, aerofoil profile is close
Stall edge, the lift coefficient of aerofoil profile increases 10.1% after optimization, and corresponding lift resistance ratio improves 3.84%, therefore, passes through
Above-mentioned conclusion can see, which can effectively promote the aeroperformance of aerofoil profile, for the engineering design in terms of aerofoil profile
Tool has very great help.
Claims (10)
1. a kind of method for low Reynolds number airfoil optimization, it is characterised in that steps are as follows:
(1) according to mission requirements, CST function is compiled on Matlab software, is parameterized aerofoil profile with CST function, input CST letter
Parameter in number obtains the geometric shape of the corresponding aerofoil profile of CST function；
(2) geometric shape of aerofoil profile is imported into ICEM software, using the macro recording function of ICEM, completes the finite element grid to aerofoil profile
It divides, obtains grid file；
(3) it carries out macro recording in Fluent software flight operating condition, Pneumatic Calculation are solved equation and be configured, by grid text
Part imports Fluent software, completes Pneumatic Calculation, obtains lift coefficient, lift resistance ratio when aerofoil profile cruise；
(4) lift coefficient, lift resistance ratio judge when the aerofoil profile obtained to step (3) is cruised, if lift coefficient when aerofoil profile is cruised,
Lift resistance ratio is all satisfied mission requirements, then retains the corresponding CST function of geometric shape of aerofoil profile in step (1)；Otherwise, return step
(1) parameter in CST function is adjusted.
2. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: geometric shape,
Thickness, camber and leading-edge radius including aerofoil profile.
3. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: the CST of compiling
Function, including classification functionAnd shape functionTwo parts are multiplied to obtain CST function, the song of CST function representation
Line is capable of the shape of accurate description low Reynolds number airfoil.
4. a kind of method for low Reynolds number airfoil optimization according to claim 3, it is characterised in that: input CST letter
Parameter in number, specifically: in CST functionConstant after parameter input in part, the parameter in S (ψ) can be adjusted
It is whole.
5. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: macro using ICEM
Recording function completes the FEM meshing to aerofoil profile, specifically: full structured grid is used when grid dividing, sets aerofoil profile
Far field front, top, lower section distance, rear distance, grid height.
6. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: grid file
For .mesh format.
7. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: to flight work
Condition, Pneumatic Calculation solve equation and are configured, specifically: the setting of flight operating condition includes: the flying height of mission requirements, flight speed
Degree, flight attitude；It includes the equation for simulating aerofoil profile Laminar Flow, transition prediction, turbulent flow that Pneumatic Calculation, which solves equation,.
8. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: complete pneumatic meter
It calculates, obtains wing section lift coefficient, lift resistance ratio, specifically: utilize the side for simulating aerofoil profile Laminar Flow, transition prediction, turbulent flow
Journey obtains lift coefficient, lift resistance ratio when aerofoil profile cruise.
9. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: step (4) is right
When lift coefficient, lift resistance ratio are judged when the aerofoil profile cruise that step (3) obtains, mission requirements include cruising lift coefficient most
The minimum value of small value and lift resistance ratio, lift coefficient is respectively greater than the cruise liter of mission requirements when the aerofoil profile that step (3) obtains is cruised
The minimum value of force coefficient and the minimum value of lift resistance ratio are judged to meeting mission requirements.
10. a kind of method for low Reynolds number airfoil optimization according to claim 1, it is characterised in that: step (4) is returned
The parameter in step (1) adjustment CST function is returned, specifically: it will be in CST functionParameter in part remains unchanged,
AdjustmentIn parameter.
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| CN115593612A (en) * | 2022-12-15 | 2023-01-13 | 中国空气动力研究与发展中心空天技术研究所（Cn） | Self-leveling anti-stall high-performance airfoil |
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| CN115593612B (en) * | 2022-12-15 | 2023-04-25 | 中国空气动力研究与发展中心空天技术研究所 | Self-balancing stall-resistant high-performance airfoil |
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