CN106021808A - Low span chord ratio aerofoil type designing method considering three-dimensional effect - Google Patents
Low span chord ratio aerofoil type designing method considering three-dimensional effect Download PDFInfo
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Abstract
The invention provides a low span chord ratio aerofoil type designing method considering a three-dimensional effect. The method sequentially comprises the steps of building parameterized initial foil type data; determining a foil type design status and a designed target; adopting a Latin hypercube sampling method, a plurality of sample foil type data is obtained; building an agent model; building an optimization population and adopting a multi-target optimization algorithm for optimizing the optimization population. With the combination of a classic foil-type parameterizing method, the agent model technology and the multi-target optimization algorithm, the efficient and reliable fighter low-span-chord ratio aerofoil type designing method, the low span chord ratio aerofoil type performance is ensured through foil type geometric and aerodynamic pneumatic performance under the two-dimensional environment, the transonic speed and the supersonic speed performance of a aerofoil can be greatly improved through the foil type designed by the model, and the voyage and operation radius are increased while the aero supersonic speed cruising capacity is improved.
Description
Technical field
The present invention relates to air-foil design field, and Computer Simulation and numerical optimization technique field, specifically
For a kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect.
Background technology
For high aspect ratio wing, the aerodynamic characteristic on aerofoil surface major part area is close to two-dimensional flow, Three-dimensional Flow
Only at wing root and tip station, therefore, the aerodynamic characteristic of aerofoil profile will determine the aerodynamic characteristic of whole wing, and the selection of aerofoil profile is to greatly
Aspect ratio wing design is particularly significant.For modern advanced fighter and high motor-driven unmanned plane, typically require from subsonic speed to super
All having superior performance in the range of velocity of sound, therefore wing typically uses the thin wing in the big angle of sweep of low aspect ratio.For little Zhan
String ratio or highly sweptback wing, universal is considered, and the three-dimensional that the leading edge of a wing or lateral margin are rolled separates whirlpool and their stream fields
Inducing action, make the maximum lift coefficient of wing improve a lot, the aerodynamic force of High Angle of Attack lower wing had conclusive
Affecting, these are very different with the high aspect ratio wing separated flow form with two-dimensional closed type Disengagement zone as principal character,
It is less on low aspect ratio wing impact that this allows for aerofoil profile maximum lift characteristic and stalling characteristics.Therefore pneumatic at this kind of wing
In design, it is considered that the flat shape of wing plays decisive role, and aerofoil profile importance reduces, and generally uses relative thickness
Less than 6% and the sharper little camber aerofoil profile of head, emphasis carries out flat shape, bending and thickness modification design.
But in real aircraft design process, it has been found that for low aspect ratio wing, although preponderate with Three-dimensional Flow
For its feature, but aerofoil profile is the most highly important to low aspect ratio wing design, because: the transonic speed lifting resistance characteristic of aerofoil profile is straight
Connecing and affect flight, supersonic drag characteristic directly affects the supersonic cruise ability of aircraft, the direct shadow of camber of aerofoil profile
Ring the maneuverability of aircraft.The leading edge shape of aerofoil profile can affect the three-dimensional generation of vortex sheet, development and the position in whirlpool of separating, permissible
Affect vortex lift and leading edge suction, thus affect the High Angle of Attack lifting resistance characteristic of aircraft.Even if the supercritical performance of aerofoil profile is to little Zhan
String the most still has directly impact than wing, and the fighter plane of modern high maneuverability does not require nothing more than aerofoil profile used and has high maximum
Lift, but also require that aerofoil profile has big lift-drag ratio when bigger lift coefficient.The drag divergence border of aerofoil profile, lift tremble battle array
Border, still the performance on wing has important impact.Therefore, even if to low aspect ratio or highly sweptback wing, the selection of aerofoil profile
With the important content that design remains airplane design.
Traditional Airfoil Design method for low aspect ratio wing inapplicable, this is because:
For ultrasonic state, the pressure distribution of wing various location aerofoil profile is essentially identical, the result of two-dimensional design
Keeping consistent with three-dimensional assessment result, because in the case of supersonic speed, the flowing of aerofoil surface is mainly two-dimensional flow, three-dimensional
Effect is inconspicuous, it is easy to extract the design objective of aerofoil profile from the design objective of wing.On the other hand, low aspect ratio wing
Supersonic drag mostlys come from supersonic drag, therefore can reach Supersonic by the zero lift drag of Airfoil Design reduction wing
The purpose of design of speed drag reduction.
Under transonic state, the pressure distribution of wing various location aerofoil profile is completely different, with the pressure of dimensional airfoil
Power distribution also greatly differs from each other, it is also difficult to find the relation between aerofoil profile and the design point of wing.Therefore, the low aspect ratio wing wing
The design of type can not be solved by traditional method, and the design point of the two is inconsistent, causes design result trend contrary.Another
Aspect, the main reduction of design of aerofoil profile is drag due to shock wave i.e. zero lift drag, for low aspect ratio wing, lures in the case of transonic speed
Lead resistance and account for major part.Therefore low aspect ratio wing in the case of transonic speed, can not be protected by the design of traditional dimensional airfoil
The correctness of card design result.
In order to consider the impact of wing three-dismensional effect, the present invention is Airfoil Design when, by the pact to off-design point
In the middle part of bundle, aerofoil profile, the constraint of camber, considers the impact of wing three-dismensional effect, thus ensures low aspect ratio wing Airfoil Design
Effectiveness.The target generally supersonic cruise resistance and transonic speed cruise drag designed as optimization, to improve the super of aircraft
Subsonic cruise ability increases voyage and combat radius simultaneously.
Summary of the invention
The present invention proposes a kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, by under two-dimensional environment
Geometry and pneumatic Performance Constraints to aerofoil profile ensure aerofoil profile performance on low aspect ratio wing, in conjunction with classical aerofoil optimization
Method for designing, constructs the fighter plane low aspect ratio wing Airfoil Design method of high efficient and reliable, has the highest practical value.
The technical scheme is that
A kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that: include following step
Rapid:
Step 1: set up parameterized initial aerofoil profile data；
Step 2: determine design point and the design object of aerofoil profile, be divided into
Transonic speed design point: Ma=0.85, Cl=0.27 minimize:Cd；With
Supersonic design point: Ma=1.5, Cl=0.1 minimize:Cd；
Wherein Ma is Mach number, and Cl is lift coefficient, and Cd is resistance coefficient；
Step 3: the initial aerofoil profile data obtained according to step 1 parameterized treatment, uses Latin hypercube sampling method to obtain
Obtain some sample aerofoil profile data；And all sample aerofoil profiles are carried out flow field calculation, wherein the design point of flow field calculation is step 2
The middle Airfoil Design state determined；
Step 4: the some sample aerofoil profile data obtained according to step 3 and the flow field calculation result of each sample aerofoil profile, builds
Vertical agent model；
Step 5: setting up and optimize population, comprise some sample points in described optimization population, described sample point is for meeting little Zhan
String is than the parametrization aerofoil profile data of air-foil geometrical constraint；Multi-objective optimization algorithm is used to carry out optimizing to optimizing population, excellent
Changing target is:
For the design point of Ma=0.85, Cl=0.27, the Cd of optimum results aerofoil profile gets minimum, and for Ma=
The design point of 1.5, Cl=0.1, the Cd of optimum results aerofoil profile gets minimum；
Simultaneously during optimizing, the satisfied following constraint of optimum results aerofoil profile:
During Ma=0.25, the maximum lift coefficient of optimum results aerofoil profile is not less than setting value；
During Ma=0.85, the lift-drag ratio under 7 degree of angles of attack of optimum results aerofoil profile is not less than setting value；
The maximum gauge of optimum results aerofoil profile is not less than setting value；
During Ma=0.75, optimum results profile drag coefficient is not higher than setting value；
During Ma=1.2, optimum results profile drag coefficient is not higher than setting value；
In the middle part of optimum results aerofoil profile, camber is not less than setting value；
In searching process, use the flow field result of sample point in the agent model calculation optimization population of step 4 foundation.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: if step 5 is not met for the optimum results of constraint, then change the setting of camber in the middle part of corresponding optimum results aerofoil profile
Value, re-starts searching process.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: in step 5, multi-objective optimization algorithm obtains Pareto disaggregation, Pareto is solved the series aerofoil sections concentrated and is separately to
On low aspect ratio wing, compare transonic speed and the supersonic performance of low aspect ratio wing, obtain the low aspect ratio wing wing of optimum
Type.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: the transonic speed of low aspect ratio wing and supersonic performance are drag characteristic.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: setting up parameterized initial aerofoil profile data procedures in step 1 is: the existing aerofoil profile of selection is as initial aerofoil profile, and uses
Parametric method carries out parameterized treatment to initial aerofoil profile.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: setting up parameterized initial aerofoil profile data procedures in step 1 is: according to the geometrical constraint of low aspect ratio wing aerofoil profile,
Parametric method is used to design initial aerofoil profile.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: parametric method is B-spline method.
Further preferred version, a kind of described low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is special
Levy and be: the agent model in step 4 is Kriging agent model.
Beneficial effect
The present invention breaches the method for the three-dismensional effect not considering wing in traditional airfoil design, for fighter plane little Zhan string
Compare wing, it is proposed that consider wing three-dismensional effect multiple target Aerodynamic optimization design model, by under two-dimensional environment to aerofoil profile
Geometry and pneumatic Performance Constraints ensure aerofoil profile performance on low aspect ratio wing.In conjunction with classical aerofoil profile parametric method,
Agent model technology, multi-objective optimization algorithm, construct the fighter plane low aspect ratio wing Airfoil Design method of high efficient and reliable, logical
The aerofoil profile crossing this modelling can be greatly improved transonic speed and the supersonic performance of wing, improves the supersonic cruise energy of aircraft
Power increases voyage and combat radius simultaneously.
The additional aspect of the present invention and advantage will part be given in the following description, and part will become from the following description
Obtain substantially, or recognized by the practice of the present invention.
Accompanying drawing explanation
Above-mentioned and/or the additional aspect of the present invention and advantage are from combining the accompanying drawings below description to embodiment and will become
Substantially with easy to understand, wherein:
Fig. 1 B-spline basic function；
Fig. 2 B-spline curves matching aerofoil profile；
Fig. 3 agent model test function；
Fig. 4 agent model anticipation function；
Fig. 5 test function contour map；
Fig. 6 anticipation function contour map；
The Pareto leading edge of Fig. 7 real function；
The Pareto leading edge that Fig. 8 multi-objective particle swarm algorithm searches；
Fig. 9 typical battle machine plane graph；
Figure 10 considers the aerofoil profile of design under different three-dismensional effects；
The near-sonic drag characteristic of the lower designing airfoil of Figure 11 difference camber constraint；
The supersonic drag characteristic of the lower designing airfoil of Figure 12 difference camber constraint；
The lower designing airfoil near-sonic drag characteristic on low aspect ratio wing of Figure 13 difference camber constraint；
The lower designing airfoil supersonic drag characteristic on low aspect ratio wing of Figure 14 difference camber constraint；
Figure 15 considers the aerofoil profile aerodynamic optimization design process of three-dismensional effect.
Detailed description of the invention
Embodiments of the invention are described below in detail, and described embodiment is exemplary, it is intended to be used for explaining the present invention, and
It is not considered as limiting the invention.
Modern advanced fighter typically requires all have superior performance, therefore machine in subsonic speed to ultrasonic scope
The wing typically uses the thin wing in the big angle of sweep of low aspect ratio.In the pneumatic design of this kind of wing, preponderate for it with Three-dimensional Flow
Feature, it is considered that the flat shape of wing plays decisive role, but low aspect ratio wing is designed the most very by aerofoil profile
Important: the transonic speed lifting resistance characteristic of aerofoil profile directly affects flight, and supersonic drag characteristic directly affects the super of aircraft
Subsonic cruise ability, the camber of aerofoil profile directly affects the maneuverability of aircraft.If not considering wing three in the design of aerofoil profile
The impact of dimension effect, is applied on low aspect ratio wing to lose efficacy by the aerofoil profile of two-dimensional design, and especially induced drag accounts for master
The wing near-sonic drag led.To this end, the present invention proposes a kind of low aspect ratio wing Airfoil Design side considering three-dismensional effect
Method, by the different constraints to aerofoil profile, it is considered to after the three-dismensional effect of wing, re-establish Aerodynamic optimization design model, pneumatic excellent
Change the aerofoil profile after design and be applied on low aspect ratio wing that there is superior performance, the transonic speed of wing and supersonic cruise ability
All it is greatly improved.
The present embodiment comprises the following steps:
Step 1: set up parameterized initial aerofoil profile data.
The most both by the existing aerofoil profile of selection as initial aerofoil profile, and can use parametric method that initial aerofoil profile is carried out
The mode of parameterized treatment obtains parameterized initial aerofoil profile data, it is also possible to according to the geometry of low aspect ratio wing aerofoil profile about
Bundle, uses parametric method to design initial aerofoil profile and obtains parameterized initial aerofoil profile data.
In the present embodiment, use classical NACA64A aerofoil profile as initial aerofoil profile, use B-spline method to initial aerofoil profile
Carry out parametrization.B-spline curves have the theoretical basis of good locality, motility and maturation, de Boor and Cox lead
The B-spline basic function of the recursive definition gone out is represented by:
In formula, k represents the power of B-spline, and t is node, and subscript i is the sequence number of B-spline, and arranges 0/0=0.Any one
B-spline curves can be by B-spline basic function and controlling polygon summit CiLinear combination represents.
B-spline method can refer to existing document: Zhu Xinxiong. Free Curves and Surfaces Modeling Technology. and Beijing: scientific publication
Society, 2000.
Step 2: determine design point and the design object of aerofoil profile, fighter plane low aspect ratio aerofoil profile mainly have supersonic speed and across
Two design points of subsonic cruise, are divided into:
Transonic speed design point: Ma=0.85, Cl=0.27 minimize:Cd；With
Supersonic design point: Ma=1.5, Cl=0.1 minimize:Cd；
Wherein Ma is Mach number, and Cl is lift coefficient, and Cd is resistance coefficient.
Step 3: the initial aerofoil profile data obtained according to step 1 parameterized treatment, uses Latin hypercube sampling method to obtain
Obtain some sample aerofoil profile data；And use CFD approach to carry out flow field calculation, the wherein design of flow field calculation all sample aerofoil profiles
State is the Airfoil Design state determined in step 2.
Using Latin hypercube to carry out EXPERIMENTAL DESIGN, under transonic speed and supersonic speed calculating state, sampling is originally.LHS chooses
Sample is distributed at whole design variable space uniform, is characterized in the one-dimensional projection in office of all samples all not having repetition values,
Projection respectively falls in the subinterval identical with number of samples, and these subintervals are full of whole design variable space and uniformly divide
Cloth；Which subinterval projection as each sample falls in, then be random assortment.Sample selected by assuming is x(i) j
(i=1 ..., n；J=1 ..., m), n is sample size, and m is the design variable number i.e. dimension of sample.LHS method chooses sample
Point can be realized by following algorithm:
U in formulaj、LjIt is respectively the upper limit value and lower limit value of jth design variable, R(i) jIt is the random integers between 0 to n, r(i) j
It it is the random number between 0 to 1.In formula, R(i) jDetermine sample x(i) jFall in which subinterval, and r(i) jDetermine this son
Which position in interval.
Latin hypercube sampling method refers to existing document: Zhang Dehu. agent model sampling criterion research. and aerodynamic
Journal 2011.
Step 4: the some sample aerofoil profile data obtained according to step 3 and the flow field calculation result of each sample aerofoil profile, builds
Vertical agent model.In the present embodiment, agent model is Kriging agent model.
Kriging model is the unbiased esti-mator model that stochastic process estimate variance is minimum, dynamic with known sample information
It is configured to basis and fully takes into account variable correlation properties spatially, set up the approximate function of object to simulate certain point
Unknown message.
Kriging, as the interpolation technique of a kind of half parametric, contains argument section (regression analysis) and nonparametric portion
Divide (random distribution): multinomial and random distribution
Y=F (β, x)+z (x)=fT(x)β+z(x)
Wherein β is regression coefficient, and f (x) is the multinomial of x, in design space, it is provided that the overall situation approximation of simulation, permissible
It is 0 rank, single order or second order polynomial；Z (x) is the error of random distribution, it is provided that the approximation to simulation partial deviations, has as follows
Statistical property:
E (z (x))=0
Var [z (x)]=σz 2
Cov[z(xi),z(xj)]=σz 2[Rij(θ,xi,xj)]
X in formulaiAnd xjIt is any two point in training sample, Rij(θ,xi,xj) it is the correlation function with parameter θ, table
Levy the spatial coherence between training sample point.
Given training sample set S=[x1,x2,…xn] and response collection Y=[y1,y2,…yn], it was predicted that the response value of point can
To be expressed as:
Kriging agent model refers to existing document: the high moonlight: Optimization Design based on kriging agent model
And the application .2009 in injection mo(u)lding.
Step 5: setting up and optimize population, comprise some sample points in described optimization population, described sample point is for meeting little Zhan
String is than the parametrization aerofoil profile data of air-foil geometrical constraint；Multi-objective optimization algorithm is used to carry out optimizing to optimizing population, excellent
Changing target is:
For the design point of Ma=0.85, Cl=0.27, the Cd of optimum results aerofoil profile gets minimum, and for Ma=
The design point of 1.5, Cl=0.1, the Cd of optimum results aerofoil profile gets minimum；
Simultaneously during optimizing, the satisfied following constraint of optimum results aerofoil profile:
During Ma=0.25, the maximum lift coefficient of optimum results aerofoil profile is not less than setting value；
During Ma=0.85, the lift-drag ratio under 7 degree of angles of attack of optimum results aerofoil profile is not less than setting value；
The maximum gauge of optimum results aerofoil profile is not less than setting value；
During Ma=0.75, optimum results profile drag coefficient is not higher than setting value；
During Ma=1.2, optimum results profile drag coefficient is not higher than setting value；
In the middle part of optimum results aerofoil profile, camber is not less than setting value；
Rear 3 item constraint purposes are the impacts in order to eliminate the three-dismensional effect such as angle of sweep and aspect ratio.
In the present embodiment, the setting value of front 5 item constraints uses the respective value of initial aerofoil profile, it may be assumed that
During Ma=0.25, the maximum lift coefficient of optimum results aerofoil profile is not less than 0.9；
During Ma=0.85, the lift-drag ratio under 7 degree of angles of attack of optimum results aerofoil profile is not less than 7.5；
The maximum gauge of optimum results aerofoil profile is not less than 0.04；
During Ma=0.75, optimum results profile drag coefficient is not higher than 0.0058；
During Ma=1.2, optimum results profile drag coefficient is not higher than 0.0269.
For the 6th item constraint, refer in the middle part of aerofoil profile be in 25%～75% chord length scope aerofoil profile, corresponding optimization in the present embodiment
In the middle part of result aerofoil profile, the setting value of camber is 0.005.If optimized algorithm is not met for the optimum results of constraint, then it is right to change
Answer the setting value of camber in the middle part of optimum results aerofoil profile, re-start searching process.
In searching process, use the flow field result of sample point in the agent model calculation optimization population of step 4 foundation.
In the present embodiment, multi-objective optimization algorithm obtains Pareto disaggregation, and Pareto solution refers to of multi-objective problem
The solution of " not bad ", so being also efficient solution, noninferior solution or acceptable solution.It is multiobjective optimization research in one most basic
Concept.For maximization problem, the definition that Pareto solves is: for feasible solution X*
A () and if only if there is not feasible solution X, make fi(X)≥fi(X*),i∈{1,…,n}
(b) at least exist a j ∈ 1 ..., n}, make fi(X)≥fi(X*)
When two conditions are set up, then feasible solution X*It it is a Pareto optimal solution.
Multi-objective particle swarm refers to existing document: Wang Rongwei: optimized algorithm and the applied research in aerodynamic optimization thereof
.2011。
By Pareto solve concentrate series aerofoil sections be separately on low aspect ratio wing, compare low aspect ratio wing across
Velocity of sound and supersonic performance, transonic speed and supersonic performance here are drag characteristic, as shown in Figure 13 and Figure 14, are considered
The optimum low aspect ratio wing aerofoil profile of three-dismensional effect.
Although above it has been shown and described that embodiments of the invention, it is to be understood that above-described embodiment is example
Property, it is impossible to be interpreted as limitation of the present invention, those of ordinary skill in the art is without departing from the principle of the present invention and objective
In the case of above-described embodiment can be changed within the scope of the invention, revise, replace and modification.
Claims (8)
1. the low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that: comprise the following steps:
Step 1: set up parameterized initial aerofoil profile data；
Step 2: determine design point and the design object of aerofoil profile, be divided into
Transonic speed design point: Ma=0.85, Cl=0.27 minimize:Cd；With
Supersonic design point: Ma=1.5, Cl=0.1 minimize:Cd；
Wherein Ma is Mach number, and Cl is lift coefficient, and Cd is resistance coefficient；
Step 3: the initial aerofoil profile data obtained according to step 1 parameterized treatment, if using Latin hypercube sampling method to obtain
Dry sample this aerofoil profile data；And all sample aerofoil profiles are carried out flow field calculation, during wherein the design point of flow field calculation is step 2 really
Fixed Airfoil Design state；
Step 4: the some sample aerofoil profile data obtained according to step 3 and the flow field calculation result of each sample aerofoil profile, sets up generation
Reason model；
Step 5: setting up and optimize population, comprise some sample points in described optimization population, described sample point is for meeting low aspect ratio
The parametrization aerofoil profile data of air-foil geometrical constraint；Use multi-objective optimization algorithm to carry out optimizing to optimizing population, optimize mesh
It is designated as:
For the design point of Ma=0.85, Cl=0.27, the Cd of optimum results aerofoil profile gets minimum, and for Ma=1.5, Cl
The design point of=0.1, the Cd of optimum results aerofoil profile gets minimum；
Simultaneously during optimizing, the satisfied following constraint of optimum results aerofoil profile:
During Ma=0.25, the maximum lift coefficient of optimum results aerofoil profile is not less than setting value；
During Ma=0.85, the lift-drag ratio under 7 degree of angles of attack of optimum results aerofoil profile is not less than setting value；
The maximum gauge of optimum results aerofoil profile is not less than setting value；
During Ma=0.75, optimum results profile drag coefficient is not higher than setting value；
During Ma=1.2, optimum results profile drag coefficient is not higher than setting value；
In the middle part of optimum results aerofoil profile, camber is not less than setting value；
In searching process, use the flow field result of sample point in the agent model calculation optimization population of step 4 foundation.
A kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that:
If step 5 is not met for the optimum results of constraint, then change the setting value of camber in the middle part of corresponding optimum results aerofoil profile, again
Carry out searching process.
A kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that:
In step 5, multi-objective optimization algorithm obtains Pareto disaggregation, Pareto is solved the series aerofoil sections concentrated and is separately to little Zhan string
Ratio, on wing, compares transonic speed and the supersonic performance of low aspect ratio wing, obtains the low aspect ratio wing aerofoil profile of optimum.
A kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that:
The transonic speed of low aspect ratio wing and supersonic performance are drag characteristic.
A kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that:
Setting up parameterized initial aerofoil profile data procedures in step 1 is: the existing aerofoil profile of selection is as initial aerofoil profile, and uses parametrization side
Method carries out parameterized treatment to initial aerofoil profile.
A kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that:
Setting up parameterized initial aerofoil profile data procedures in step 1 is: according to the geometrical constraint of low aspect ratio wing aerofoil profile, uses parameter
Change method designs initial aerofoil profile.
7., according to the low aspect ratio wing Airfoil Design method considering three-dismensional effect a kind of described in claim 5 or 6, its feature exists
In: parametric method is B-spline method.
A kind of low aspect ratio wing Airfoil Design method considering three-dismensional effect, it is characterised in that:
Agent model in step 4 is Kriging agent model.
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| CN110104164A (en) * | 2019-05-16 | 2019-08-09 | 北京理工大学 | A kind of preceding load for Transonic Wing-air-breathing combination flow control method |
| CN110334449A (en) * | 2019-07-04 | 2019-10-15 | 南京航空航天大学 | A kind of aerofoil profile Fast design method based on online agent model algorithm |
| CN110705126A (en) * | 2019-10-24 | 2020-01-17 | 南京航空航天大学 | Helicopter rotor wing profile determining method and system |
| CN111666630A (en) * | 2020-05-26 | 2020-09-15 | 煤炭科学研究总院 | Multi-objective intelligent optimization design method for underground coal mine unmanned aerial vehicle structure |
| CN111859545A (en) * | 2020-07-27 | 2020-10-30 | 西北工业大学 | Wide-speed-range high-lift-drag-ratio wing optimal design method considering lift matching |
| CN112926132A (en) * | 2021-01-28 | 2021-06-08 | 西北工业大学 | Fixed wing airfoil aerodynamic shape design method considering influence of three-dimensional effect |
| CN112926148A (en) * | 2021-01-28 | 2021-06-08 | 西北工业大学 | Propeller airfoil aerodynamic shape design method considering influence of three-dimensional effect |
| CN113626935A (en) * | 2021-08-16 | 2021-11-09 | 成都飞机工业（集团）有限责任公司 | Design method of transonic crescent wing with high cruising efficiency |
| 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 |
| CN116341097A (en) * | 2022-02-07 | 2023-06-27 | 西北工业大学 | Transonic wing optimal design method based on novel high-dimensional proxy model |
| CN117910150A (en) * | 2024-03-20 | 2024-04-19 | 西北工业大学 | Transonic wing profile design method and system for sweepback wings of aircraft |
| CN117910150B (en) * | 2024-03-20 | 2024-05-31 | 西北工业大学 | Transonic wing profile design method and system for sweepback wings of aircraft |
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| CN106777590A (en) * | 2016-11-30 | 2017-05-31 | 中国航空工业集团公司沈阳飞机设计研究所 | A kind of air-foil matches method for designing |
| CN107679294A (en) * | 2017-09-18 | 2018-02-09 | 西安交通大学 | A kind of board-like heat exchanger inlet and outlet design method of multichannel |
| CN107679294B (en) * | 2017-09-18 | 2019-04-12 | 西安交通大学 | A kind of board-like heat exchanger inlet and outlet design method of multichannel |
| CN110104164A (en) * | 2019-05-16 | 2019-08-09 | 北京理工大学 | A kind of preceding load for Transonic Wing-air-breathing combination flow control method |
| CN110104164B (en) * | 2019-05-16 | 2020-08-11 | 北京理工大学 | Front loading-air suction combined flow control method for transonic airfoil |
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| CN111666630B (en) * | 2020-05-26 | 2023-05-09 | 煤炭科学研究总院 | Multi-target intelligent optimization design method for underground coal mine unmanned aerial vehicle structure |
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| CN112926132B (en) * | 2021-01-28 | 2022-11-04 | 西北工业大学 | Fixed wing airfoil aerodynamic shape design method considering influence of three-dimensional effect |
| CN112926148B (en) * | 2021-01-28 | 2023-02-03 | 西北工业大学 | Propeller airfoil aerodynamic shape design method considering influence of three-dimensional effect |
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| CN113626935A (en) * | 2021-08-16 | 2021-11-09 | 成都飞机工业（集团）有限责任公司 | Design method of transonic crescent wing with high cruising efficiency |
| CN113626935B (en) * | 2021-08-16 | 2023-09-29 | 成都飞机工业（集团）有限责任公司 | Design method of transonic moon-shaped wing with high cruising efficiency |
| CN116341097A (en) * | 2022-02-07 | 2023-06-27 | 西北工业大学 | Transonic wing optimal design method based on novel high-dimensional proxy model |
| CN116341097B (en) * | 2022-02-07 | 2023-09-12 | 西北工业大学 | Transonic wing optimal design method based on novel high-dimensional proxy model |
| 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 |
| 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 |
| CN117910150A (en) * | 2024-03-20 | 2024-04-19 | 西北工业大学 | Transonic wing profile design method and system for sweepback wings of aircraft |
| CN117910150B (en) * | 2024-03-20 | 2024-05-31 | 西北工业大学 | Transonic wing profile design method and system for sweepback wings of aircraft |
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