CN111563354A - Icing wind tunnel test similarity conversion method based on numerical simulation - Google Patents
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Abstract
The invention discloses a numerical simulation-based icing wind tunnel test similarity conversion method, which comprises the steps of calculating parameters required by a test through similarity criteria, and if the parameters exceed the icing wind tunnel capacity envelope range, adjusting the parameters to enable the parameters to meet the icing wind tunnel capacity envelope range; performing analog calculation on the states before and after conversion through CFD software, and comparing the ice type calculation results before and after conversion to evaluate whether the conversion results meet the requirements or not; if the difference between the ice types before and after conversion is larger than the comparison display of the calculation result, the parameters are reselected. By the method, accurate simulation and experiment results can be obtained within the range of the existing icing wind tunnel capability envelope, and the performance requirements on the icing wind tunnel are reduced.
Description
Technical Field
The application relates to the field of numerical simulation, in particular to numerical simulation of an icing wind tunnel experiment.
Background
The icing wind tunnel test is an important means for evaluating the safety performance of the aircraft, and the influence of the icing of the aircraft on the flight performance or the performance of an anti-icing and anti-icing system of the aircraft can be obtained by the test method. For a larger aircraft or component model, the current main icing wind tunnels in the world cannot be subjected to full-scale tests, so the model needs to be scaled. In order to obtain the ice type geometrically similar to the original size by the icing wind tunnel test of the scaling model, the test conditions need to be similarly converted. The similarity transformation method is an analysis method implemented by taking a scaling model as an object, and is used for calculating the test state parameters through a series of similarity criterion numbers and obtaining a test result which is as close to an original target state as possible.
Common similar transformation methods include Ruff method, ONERA method, Olsen method, and the like. The various conversion methods more or less ensure that the number of similarity criteria is equal, and generally, the more the number of similarity criteria satisfying the same is, the closer the target state is. The Ruff method can ensure that at least five similar criteria are equal in number, and a large number of tests and verifications are carried out in the IRT wind tunnel of the NASA, and the result shows that the Ruff method can obtain a state closer to an original target state at most. The Ruff method advocates that the weber number WeL of the diameter of the front edge is used as the wind speed basis of the conversion state, and the energy transfer potential of the water drop with the relative thermal coefficient is used as the temperature basis of the conversion state. However, the use of the Ruff method has many limitations, and the use of WeL as a speed selection basis necessarily results in an increase in post-conversion speed: the higher the speed is, the more uneven the cloud and fog field of the icing wind tunnel is; meanwhile, the MVD can be reduced and even exceed the capability range of the icing wind tunnel.
Disclosure of Invention
The application aims to provide a novel similarity transformation method so as to improve the practicability of similarity transformation.
The application is realized by adopting the following technical scheme: a numerical simulation-based icing wind tunnel test similarity conversion method comprises the following steps: (1) calculating the wind speed of the model under the icing experimental condition through similar criteriaV s And median diameter of water droplet s (ii) a (2) Examination ofV s And s whether the wind tunnel capacity is within the range of the icing wind tunnel capacity envelope or not; if it exceeds the icing wind tunnel capability envelope, the pairV s And s adjusting to meet the icing wind tunnel capacity envelope range; entering the next step after the icing wind tunnel capacity envelope range is met; (3) calculating the static temperature T of the air flow under the experimental condition of model icingst,SAnd liquid water content LWC; (4) examination Tst,SWhether the LWC is within the icing wind tunnel capacity envelope or not; if it exceeds the icing wind tunnel capability envelope, for Tst,SThe LWC is adjusted to accord with the icing wind tunnel capacity envelope range; entering the next step after the icing wind tunnel capacity envelope range is met; (5) calculating icing time of the model under icing experimental conditionsτ s (ii) a (6) Performing analog calculation on the states before and after conversion by using CFD software, and comparing the ice type calculation results before and after conversion to evaluate whether the conversion results meet the requirements or not; and if the similarity degree of the ice types before and after conversion is less than 90% in comparison and display of the calculation result, the parameters are selected again.
In the step (1), theV s By similar normWe L It is determined that,We L is defined as follows:
by (a)W eL )s=(W eL )rCalculate outV s ，
Where ρ iswIn order to be the density of the droplets,Lin order to be a characteristic dimension of the device,Vas the speed of impact of the water droplets, σ awIs the surface tension coefficient of water drop, s is the experimental condition of model icing, and r is of full-size objectReference is made to icing conditions.
In the step (1), the s By similar normK 0 It is determined that,K 0 is defined as follows:
by (a)K 0 )s=(K 0 )rCalculate out s ，
Wherein,R αis the gas constant of air, is the average volume diameter of water droplets,Tis absolute temperature, μαIs the viscosity coefficient of air;Pis the pressure;dis 2 times the diameter of the cylinder or the radius of the leading edge of the wing;k l andkis a constant.
In the step (2), ifV s And s and (3) exceeding the icing wind tunnel capacity envelope, selecting one of the following two methods for trying:
a. specifying and calculating wind speeds within any wind tunnel capability envelope s ；
b. For number of similarity criteriaK 0 Introducing tolerance, adjusting wind speed or s To the icing wind tunnel capability envelope range.
In the step (3), the Tst,SPotential transfer by water droplet energy
To determine that the user has taken a particular task,
is defined as follows:
by passing
Calculate Tst,S，
Wherein,t f is the freezing point temperature of the water,t st the air flow is static temperature;c p,ws is the specific heat capacity of the water on the frozen surface.
In the step (3), the LWC passes the freezing coefficient before and after conversionn 0 To determine that the user has taken a particular task,n 0 is defined as follows:
by (a)n 0 )s=(n 0 )rThe LWC is calculated and the calculated LWC,
wherein, Λ f Is the latent heat of freezing of the water,θconverting parameters for the energy of the airflow;bis the relative thermal coefficient.
In the step (4), if Tst,SAnd the LWC exceeds the icing wind tunnel capacity envelope, and T is selected by adopting an Olsen methodst,SAnd solving the LWC again until meeting the icing wind tunnel capacity envelope range.
In the step (5), the value of τ issDetermined by the accumulation coefficient Ac before and after conversion, defined as follows:
where ρ i is the ice density, byAc r =Ac s Calculate τs。
According to the invention, tolerance is introduced into the similarity criterion to obtain a wider conversion range, the ice type difference before and after conversion is evaluated by using a numerical simulation means, and the similarity conversion result is optimized and adjusted according to the tolerance, so that accurate simulation and experiment results can be obtained within the range of the conventional icing wind tunnel capability envelope, and the performance requirement on the icing wind tunnel is reduced. Secondly, the invention introduces a specific tolerance formula during parameter adjustment, and the convenience and the usability of the parameter adjustment are improved through the tolerance formula.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments are briefly described below, it should be understood that the following drawings only illustrate some embodiments of the present application and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained from the drawings without inventive efforts and also belong to the protection scope of the present application.
FIG. 1 is a flow chart of a similar transformation method of the present invention;
FIG. 2 is
-
A graph of the relationship;
FIG. 3 is a diagram illustrating CFD result verification for transition states according to an embodiment;
FIG. 4 is a graph of corner ice characteristics.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present application clearer, the technical solutions in the embodiments of the present application will be described below with reference to the drawings in the embodiments of the present application.
In the parameter subscripts listed below, s is the experimental condition for model icing and r is the reference icing condition for a full-size object.
Taking a certain wing with a certain chord length of 3.8m as an example, due to size limitation, a wing icing test needs to be carried out by using a scaling model, the scaling ratio of the model is 1:2, and reference working conditions are shown in table 1.
TABLE 1 reference State test
| Test parameters | Tst,S(℃) | MVD(μm) | LWC(g/m³) | H(m) | V(m/s) | chord(m) | Time（Sec) |
| Reference state | -7 | 30 | 0.268 | 3000 | 110 | 3.8 | 1350 |
An icing wind tunnel test similar conversion method based on numerical simulation is used for the above states, and as shown in fig. 1, the method comprises the following steps: (1) calculating the wind speed of the model under the icing experimental condition through similar criteriaV s And median diameter of water droplets；V s By similar normWe L It is determined that,We L is defined as follows:
known asWe L )r=2.178e+7By (1)We L )s=(We L )rCalculate outV s =155.56m/s。
Wherein,ρ w in order to be the density of the droplets,Lin order to be a characteristic dimension of the device,Vas the speed of impact of the water droplets, σ awIs the surface tension coefficient of the water drop, s is the experimental condition of model icing, and r is the reference icing condition of a full-size object.
s By similar normK 0 It is determined that,K 0 is defined as follows:
by (a)K 0 ) s =(K 0 ) r Calculate whenV s When =155.56m/s, the speed of the motor is reduced, s =16.8μm。
wherein,R α is the gas constant of air and is,is the average volume diameter of the water droplets,Tin the case of an absolute temperature,μ α is the viscosity coefficient of air;Pis the pressure;dis 2 times the diameter of the cylinder or the radius of the leading edge of the wing;k l andkis a constant.
(2) Examination ofV s And s whether the wind tunnel capacity is within the range of the icing wind tunnel capacity envelope or not; if it exceeds the icing wind tunnel capability envelope, the pairV s And s adjusting to meet the icing wind tunnel capacity envelope range; entering the next step after the icing wind tunnel capacity envelope range is met; if it isV s And s and (3) exceeding the icing wind tunnel capacity envelope, selecting one of the following two methods for trying:
a. specifying and calculating wind speeds within any wind tunnel capability envelope s (ii) a The present case adopts the method pairV s Correcting to specify the wind speed meeting the wind tunnel capacity envelopeV s =100m/s, calculated to obtain s =20.4 μm. This pair of parameters is used in subsequent calculations in this case.
b. For number of similarity criteriaK 0 Introducing tolerance, adjusting wind speed or s To the icing wind tunnel capability envelope range.
Introducing tolerance e pairsK 0 The formula is not changed, and the value range and the income are as follows:
β 0 locally collecting coefficients for stagnation points，The tolerance is usually guaranteedβ 0 The variation does not exceed 5%. When in useβ 0 When the tolerance e is not less than 0.5 percent, the value range of the tolerance e is (-9 percent)K 0 ,+11%K 0 ) Within the range ofβ 0 The change is not more than +/-5%, the value ranges of the added MVD and the added V are (-6% MVD, +7% MVD) and (-15% V, +24% V), and the MVD is the average volume diameter of the water drop.
K 0 Andβ 0 in a non-linear relationship, the value range of the tolerance is determined according toβ 0 Is determined by the actual change in the state of the vehicle. It can be seen from fig. 2 that tolerances are also introduced to the presentβ 0 The variation does not exceed +/-5 percent, inβ 0 =0.5 andβ 0 0.38, abscissaK 0 The value ranges of (A) and (B) are greatly different and reflect the value range gains of MVD and V, namelyβ 0 The smaller the gain in introducing tolerance and vice versa.
If the wind tunnel equipment cannot manufacture water drops with the particle size of 16.8 mu m, the s can be corrected by adopting a method of introducing tolerance, and if the wind tunnel equipment meets the requirement of cloud uniformity under the condition of the wind speed of 155.56m/s, the speed is directly specified. Introducing a tolerance e =11.6% K0So thatβ 0,S =105%β 0,r The correction results are shown in the following table:
TABLE 2 correction of transition State parameter Table after introducing tolerance
(3) Calculating the static temperature T of the air flow under the experimental condition of model icingst,SAnd liquid water content LWC; t isst,SPotential transfer by water droplet energy
To determine that the user has taken a particular task,
is defined as follows:
by passing
Calculate Tst,S=-6.5℃，
Wherein,t f is the freezing point temperature of the water,t st the air flow is static temperature;c p,ws is the specific heat capacity of the water on the frozen surface.
Freezing coefficient of LWC before and after conversionn 0 To determine that the user has taken a particular task,n 0 is defined as follows:
wherein,
，
by (a)n 0 )s=(n 0 )rCalculating LWC =0.417g/m ethanol,
wherein, Λ f Is the latent heat of freezing of the water,θconverting parameters for the energy of the airflow;bin order to be a relative thermal coefficient,β 0 for stationary point local collection coefficients, hcIs the convective heat transfer coefficient.
(4) Examination Tst,SWhether the LWC is within the icing wind tunnel capacity envelope or not; if the conversion result exceeds the icing wind tunnel capacity envelope, selecting T by adopting an Olsen methodst,SAnd solving the LWC again until the envelope range of the wind tunnel is met. Assuming that the wind tunnel equipment capacity in the present case cannot satisfy LWC =0.417g/m, and LWC =0.5g/m may be designated for carrying out the dry distillation, T is calculated iterativelyst,S=-7.16℃。
Assuming that the wind tunnel equipment capacity in the present case cannot satisfy LWC =0.417g/m, and LWC =0.5g/m may be designated for carrying out the dry distillation, T is calculated iterativelyst,S=-7.16℃。
(5) By passingAcThe icing time is calculated as follows:
according toAc r=Ac sIs calculated to obtain taus=477s。
The application process and the actual decision scene of the hybrid similarity transformation method are provided in the embodiment, and table 3 supplements the cases to a certain extent, and sequentially provides the transformation result of the Ruff method and two transformation results of the hybrid similarity transformation method.
Table 3 shows a table of parameters of case-by-case similarity transformation results
Table 4 shows the similarity criteria number table of case similarity transformation results
(6) Performing analog calculation on the states before and after conversion by using CFD software, and comparing the ice type calculation results before and after conversion to evaluate whether the conversion results meet the requirements or not; and if the similarity degree of the ice types before and after conversion is less than 90% in comparison and display of the calculation result, the parameters are selected again. The calculation result verification related to the present case is shown in fig. 3, and it can be found that several conversion states are close to the ice shape of the reference state, but the conversion result of the Ruff method is relatively difficult to implement, and the superiority of the hybrid similarity conversion method is reflected.
The ice type similarity degree is calculated as follows: firstly, extracting the geometrical characteristics of the ice shape, wherein the typical corner ice characteristics are defined as shown in FIG. 4, dividing the ice shape into an upper section and a lower section according to the boundary line of the airfoil shape, HuAnd HlThe length of the upper ice angle and the length of the lower ice angle are respectively defined as the farthest distance from a point on the ice shape to the surface of the wing; a. theuAnd AlRespectively defining the ice angle as the included angle formed by the length connecting line of the ice angle and the horizontal line; suAnd SlThe upper and lower icing limits are defined as the curve distance from a stagnation point to the tail end of an icing area; t issThe ice thickness at the stagnation point is defined as the normal ice thickness at the stagnation point; wmThe maximum width is defined as the maximum distance of the ice along the Y direction. The icing geometrical characteristics under most conditions can be effectively described through the 8 parameters, and when the icing appearance is a wedge streamline, the upper ice angle and the lower ice angle can not be distinguished.
Defining the difference of ice-shaped geometric characteristics as:
where X is the geometric characteristic of the ice shape, the subscript s denotes the similarly transformed ice shape, and r denotes the reference ice shape. The difference degree of different ice shape characteristics can be calculated through a formula, and the overall ice shape similarity degree is defined as:
where the subscript i denotes the different ice geometry and N denotes the number of geometries.
The above description is only a few examples of the present application and is not intended to limit the present application, and various modifications and changes may occur to those skilled in the art. Any modification, equivalent replacement, improvement and the like made within the spirit and principle of the present application shall be included in the protection scope of the present application.
Claims (9)
1. A numerical simulation-based icing wind tunnel test similarity conversion method is characterized by comprising the following steps: the method comprises the following steps: (1) calculating the wind speed of the model under the icing experimental condition through similar criteriaV s And median diameter of water droplet s (ii) a (2) Examination ofV s And s whether the wind tunnel capacity is within the range of the icing wind tunnel capacity envelope or not; if it exceeds the icing wind tunnel capability envelope, the pairV s And s adjusting to meet the icing wind tunnel capacity envelope range; entering the next step after the icing wind tunnel capacity envelope range is met; (3) calculating the static temperature T of the air flow under the experimental condition of model icingst,SAnd liquid water content LWC; (4) examination Tst,SWhether the LWC is within the icing wind tunnel capacity envelope or not; if it exceeds the icing wind tunnel capability envelope, for Tst,SThe LWC is adjusted to accord with the icing wind tunnel capacity envelope range; entering the next step after the icing wind tunnel capacity envelope range is met; (5) calculating icing time of the model under icing experimental conditionsτ s (ii) a (6) Performing analog calculation on the states before and after conversion by using CFD software, and comparing the ice type calculation results before and after conversion to evaluate whether the conversion results meet the requirements or not; and if the similarity degree of the ice types before and after conversion is less than 90% in comparison and display of the calculation result, the parameters are selected again.
2. The similarity transformation method according to claim 1, wherein in step (2), ifV s And s exceeding the icing wind tunnel capability envelope, one of the following two methods is selected for tastingTest:
a. specifying and calculating wind speeds within any wind tunnel capability envelope s ；
b. For similarity criterion number K0Introducing tolerance, adjusting wind speed or s To the icing wind tunnel capability envelope range.
3. The similarity transformation method according to claim 1, wherein in step (4), if T is Tst,SAnd the LWC exceeds the icing wind tunnel capacity envelope, and T is selected by adopting an Olsen methodst,SAnd solving the LWC again until meeting the icing wind tunnel capacity envelope range.
4. The similarity transformation method according to claim 2, wherein in step (4), if T is Tst,SAnd the LWC exceeds the icing wind tunnel capacity envelope, and T is selected by adopting an Olsen methodst,SAnd solving the LWC again until meeting the icing wind tunnel capacity envelope range.
5. The method of claim 1-4, wherein in step (1), the method comprisesV s By similar normW eL It is determined that,W eL is defined as follows:
by (a)W eL ) s =(W eL ) r Calculate outV s ，
Wherein,ρ w in order to be the density of the droplets,Lin order to be a characteristic dimension of the device,Vwhich is the speed of impact of the water droplets,σ wa is the surface tension coefficient of the water droplet,sis an experimental condition for the icing of the model,ris the reference icing condition for a full-size object.
6. A method of similarity transformation according to claim 5,characterized in that, in the step (1), the s By means of similarity criterion K0Determination of K0Is defined as follows:
by (a)K 0)s=(K 0)rCalculate out s ，
Wherein,R a is the gas constant of air and is,is the average volume diameter of the water droplets,Tin the case of an absolute temperature,μ α is the viscosity coefficient of air;Pis the pressure;dis 2 times the diameter of the cylinder or the radius of the leading edge of the wing;k l andkis a constant.
7. The similarity transformation method according to claim 6, wherein in the step (3), the Tst，SPotential transfer by water droplet energy
To determine that the user has taken a particular task,
is defined as follows:
by passing
Calculate Tst,S，
Wherein,t f is the freezing point temperature of the water,t st the air flow is static temperature;c p,ws is the specific heat capacity of the water on the frozen surface.
8. According to claim7, in the step (3), the LWC passes the freezing coefficient before and after the conversionn 0To determine that the user has taken a particular task,n 0is defined as follows:
by (a)n 0)s=(n 0)rThe LWC is calculated and the calculated LWC,
wherein, Λ f Is the latent heat of freezing of the water,θconverting parameters for the energy of the airflow;bis the relative thermal coefficient.
9. The similarity transformation method according to claim 8, wherein in the step (5), the stepτ s By accumulation factor before and after conversionAcTo determine that the user has taken a particular task,Acis defined as follows:
where ρ isiTo ice density, byAc r =Ac s Calculate outτ s 。
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| CN114169256B (en) * | 2022-02-14 | 2022-04-19 | 中国空气动力研究与发展中心低速空气动力研究所 | Method for obtaining optimal wind speed of icing wind tunnel in scaling test working condition |
| CN115048748A (en) * | 2022-08-12 | 2022-09-13 | 中国空气动力研究与发展中心低速空气动力研究所 | Method, system and processing terminal for obtaining compressor pressure prediction model |
| CN115048748B (en) * | 2022-08-12 | 2022-10-28 | 中国空气动力研究与发展中心低速空气动力研究所 | Method, system and processing terminal for obtaining compressor pressure prediction model |
| CN115524131A (en) * | 2022-09-13 | 2022-12-27 | 中国航发沈阳发动机研究所 | Complete machine anti-icing system verification method based on non-icing condition |
| CN115524131B (en) * | 2022-09-13 | 2024-03-19 | 中国航发沈阳发动机研究所 | Complete machine anti-icing system verification method based on non-icing condition |
| CN118351336A (en) * | 2024-06-17 | 2024-07-16 | 上海交通大学四川研究院 | Icing wind tunnel test similarity conversion method based on ice complexity |
| CN118351336B (en) * | 2024-06-17 | 2024-08-20 | 上海交通大学四川研究院 | Icing wind tunnel test similarity conversion method based on ice complexity |
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