CN112525474B - Method for obtaining blocking interference factor of transonic wind tunnel - Google Patents

Method for obtaining blocking interference factor of transonic wind tunnel Download PDF

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CN112525474B
CN112525474B CN202011525714.6A CN202011525714A CN112525474B CN 112525474 B CN112525474 B CN 112525474B CN 202011525714 A CN202011525714 A CN 202011525714A CN 112525474 B CN112525474 B CN 112525474B
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刘光远
史晓军
张昌荣
徐扬帆
吴继飞
黄勇
蒋鸿
李阳
杨可朋
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Ultra High Speed Aerodynamics Institute China Aerodynamics Research and Development Center
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Abstract

The invention discloses a method for obtaining a blocking interference factor of a transonic wind tunnel, which is realized based on a large-scale model and a small-scale model which have the same appearance and different scaling ratios, and comprises the following steps: respectively marking measuring points at a plurality of identical positions of the two sets of models; then, carrying out a constant Mach number variable attack angle pressure measurement test in a wind tunnel to obtain pressure coefficients of each marked measuring point of the two sets of models at different attack angles; carrying out Mach number interpolation to obtain a pressure coefficient in a nominal Mach number state; selecting k points with the minimum pressure coefficient changing along with the attack angle from the pressure coefficients under the nominal Mach number state of the small scale model, wherein k is not less than 3; selecting k points at the same positions as the small scale model from the large scale model, and calculating the differential quantity of the pressure coefficients of the k points in the large scale model and the small scale model; and (4) combining a small disturbance equation, obtaining k blockage interference factors according to the difference of the pressure coefficients, and solving an average value to obtain the blockage interference factors of the large-scale model in the current test state.

Description

Method for obtaining blocking interference factor of transonic wind tunnel
Technical Field
The invention relates to the field of experimental aerodynamics, in particular to a method for obtaining a blocking interference factor of a transonic wind tunnel.
Background
The tunnel wall interference is one of important factors influencing the quality of wind tunnel test data, and can be divided into two parts, namely blocking interference and lifting force interference according to the interference influence range, and the incoming flow speed and the model attack angle are respectively corrected. The blockage interference is a key factor influencing the wind tunnel operation and the quality of the test data, because the blockage interference not only influences the accuracy of the test data, but also causes the distortion of the inlet speed of the test section. At present, most of the main wind tunnel test mechanisms at home and abroad adopt a classical linear method or a wall pressure correction method to correct the blockage interference, but the two methods have obvious defects: the classical linear method adopts simple linear boundary conditions to simulate the test section wall plate, and then adopts a numerical method to calculate the blocking interference amount, so that a better correction effect can be realized on a low-speed solid wall or a free boundary, but the method is not suitable for air-permeable wall plates such as the hole wall and the groove wall of a transonic wind tunnel, the classical non-penetration and non-slip conditions are invalid, and the blocking interference amount of the air-permeable wall plate cannot be accurately obtained; the wall pressure information method needs to measure wall pressure distribution as boundary conditions while performing model tests, and greatly increases test difficulty and cost.
Disclosure of Invention
The invention aims to overcome the technical defects in the aspects of data correction accuracy and engineering application reliability in the prior art, and provides a method for obtaining a blocking interference factor of a transonic wind tunnel.
In order to achieve the purpose, the invention provides a method for obtaining a blocking interference factor of a transonic wind tunnel, which is realized based on a large-scale model and a small-scale model which have the same appearance and different scaling ratios, and comprises the following steps of:
respectively marking measuring points at a plurality of same positions of the large-scale model and the small-scale model;
respectively carrying out a constant Mach number variable attack angle pressure measurement test on the large-scale model and the small-scale model after the measurement points are marked in the wind tunnel to obtain pressure coefficients of the marked measurement points of the two sets of scale models under different attack angles;
performing Mach number interpolation on the pressure coefficient of each set of model to obtain the pressure coefficient in a nominal Mach number state;
selecting k points with the minimum pressure coefficient changing along with the attack angle from the pressure coefficients under the nominal Mach number state of the small scale model, wherein k is not less than 3;
selecting k points at the same position as the small scale model from the pressure coefficients of the large scale model in the nominal Mach number state, and calculating the differential quantity of the pressure coefficients of the k points corresponding to the large scale model and the small scale model;
and (4) combining a small disturbance equation, obtaining k blockage interference factors according to the difference of the pressure coefficients, and solving an average value to obtain the blockage interference factors of the large-scale model in the current test state.
As an improvement of the method, the maximum sectional area of the small-scale model is not more than 0.3 percent of the sectional area of the test section, and the sectional area of the large-scale model is not more than 1.0 percent of the sectional area of the test section.
As an improvement of the above method, the calculating step calculates the difference of the pressure coefficients of the k points in the large scale model and the small scale model; the method specifically comprises the following steps:
calculating the differential quantity delta C of the pressure coefficients of the k points corresponding to the large-scale model and the small-scale modelP,iComprises the following steps:
ΔCP,i＝CP1,i-CP2,i，i＝1,2,…,k
wherein, CP1,iIn order to select the pressure coefficient corresponding to the ith point with the minimum pressure coefficient changing along with the attack angle from the pressure coefficients under the nominal Mach number state of the small scale model, the subscript P1 represents the small scale model, CP2,iIn order to select the pressure coefficient corresponding to the ith point at the same position as the small scale model from the pressure coefficients of the large scale model in the nominal Mach number state, the subscript PAnd 2 represents a large scale model.
As an improvement of the method, the method combines a small disturbance equation to obtain k blockage interference factors according to the difference of the pressure coefficients, and an average value is obtained to obtain the blockage interference factors of the large-scale model in the current test state; the method specifically comprises the following steps:
according to the difference Delta C of the pressure coefficient by combining a small disturbance equationR,iObtaining the blockage interference factor epsilon of the ith point of the large-scale modeliComprises the following steps:
Figure BDA0002850527980000021
wherein Ma is a nominal Mach number;
the blocking interference factor epsilon of the large-scale model in the current test state is as follows:
Figure BDA0002850527980000022
compared with the prior art, the invention has the advantages that:
1. the invention provides a method for determining a blocking interference factor, which is different from a classical linear method, and adopts a new idea of comparing pressure measurement results of different scaling models, and also provides new specific requirements for the processes of test state, model incidence angle, measurement point selection and the like in comparison;
2. the method is suitable for the test sections of the transonic wall, the groove wall and other air-permeable walls, effectively expands the application range compared with the classical linear method, and simultaneously avoids the complex problem that the wall pressure distribution needs to be measured in real time by a wall pressure information method;
3. according to the method, the difference of the influence of the blocking interference on the test result is obtained by Mach number interpolation and combining the change relation of the pressure of the measuring point along with the attitude angle, so that the blocking interference factor is calculated, the change condition of the blocking interference factor along with the operation parameter can be obtained by adjusting the operation parameter of the wind tunnel, and the engineering practicability is good.
Drawings
FIG. 1 is a schematic diagram showing the comparison of the shapes of different scaling models;
FIG. 2 is a plot of small scale model profile pressure coefficient as a function of model angle of attack;
FIG. 3 is a comparison plot of the small scale model profile pressure coefficient versus the nominal Mach number before and after interpolation.
Detailed Description
According to the invention, the blockage interference is mainly reflected as the difference of model flow by-pass, so that the magnitude of the influence can be accurately evaluated by comparing test results of models with different scales in the same equipment, and further the blockage interference factor of a model with a similar configuration is obtained. Therefore, a rapid and reliable transonic wind tunnel blocking interference factor evaluation method is developed for a specific configuration model and test equipment, correction and use of test data can be effectively guided, test quality is improved, and the method has important significance for guiding wind tunnel wallboard design and parameter influence analysis.
The method provided by the invention is realized by the following technical scheme: considering that the difference between the test data of different scaling models mainly includes the influence of blocking interference, the influence of model attitude angle, the influence of test Mach number, etc., the data can be processed and corrected, and the difference of the influence of blocking interference is extracted, so as to obtain the blocking interference factor. The method mainly comprises the steps of adopting two models with the same appearance and different scaling ratios to carry out a pressure measurement test in the same wind tunnel, carrying out Mach number interpolation on original data, eliminating the difference influence of the test Mach numbers, utilizing measuring points which are insensitive to the change along with the attitude angle to carry out comparison, taking small model data as non-blocking interference influence data, and combining a small disturbance equation to obtain a blocking interference factor of a large-scaling model.
The main technical scheme of the invention is as follows:
firstly, two sets of models with different scaling ratios are utilized to respectively carry out a constant Mach number variable attack angle pressure measurement test in the same wind tunnel to obtain a variation curve of pressure coefficients of all measuring points along with an attack angle;
secondly, interpolating the test Mach number to obtain the pressure coefficient of each measuring point under the state of the nominal Mach number;
thirdly, finding k measuring points with pressure coefficients of which the root mean square deviation along with the change of the model attitude angle is less than 0.01 from all the measuring points as comparison states, wherein k is more than or equal to 3;
calculating the differential quantity delta C of the pressure coefficients of the k points corresponding to the large-scale model and the small-scale modelP,iComprises the following steps:
ΔCP,i＝CP1,i-CP2,i，i＝1,2,…,k
in the formula, CP1,iIn order to select the pressure coefficient corresponding to the ith point with the minimum pressure coefficient changing along with the attack angle from the pressure coefficients under the nominal Mach number state of the small scale model, the subscript P1 represents the small scale model, CP2,iSelecting a pressure coefficient corresponding to the ith point at the same position as the small scale model from the pressure coefficients of the large scale model in the nominal Mach number state, wherein the subscript P2 represents the large scale model;
fourthly, combining with a small disturbance equation to obtain the pressure coefficient difference delta CPA functional relationship with the occlusion interference factor epsilon;
the jam interference factor epsilon is defined as the ratio of the flow direction disturbance speed to the undisturbed flow speed at the center of the model:
Figure BDA0002850527980000041
relating speed to Mach number
Figure BDA0002850527980000042
Substituting the formula to obtain:
Figure BDA0002850527980000043
wherein u is the flow velocity, Δ u is the flow velocity difference due to the blockage disturbance, T is the gas flow temperature, Δ T is the temperature difference due to the blockage disturbance, Ma is the nominal mach number, and γ is 1.40 and is the gas constant;
according to the isentropic relation between the temperature and the Mach number, the following can be obtained:
Figure BDA0002850527980000044
thus:
Figure BDA0002850527980000045
namely:
Figure BDA0002850527980000046
the isentropic relationship between pressure and mach number yields:
Figure BDA0002850527980000047
in the formula, P is airflow pressure, and delta P is flow direction pressure difference caused by blockage interference;
the pressure coefficient of the ith measuring point of the model is as follows:
Figure BDA0002850527980000048
in the formula, PiThe pressure value of the ith measuring point of the model with different scales is obtained;
the pressure coefficient difference of the ith measuring point can be obtained as follows:
Figure BDA0002850527980000049
the above formula is developed and arranged to obtain the corresponding pressure coefficient difference Delta CP,iComprises the following steps:
ΔCP,i＝[2-(2-1.8Ma2)CP,i]εi
and fifthly, comparing the pressure coefficient difference of the large model and the small model by taking the pressure coefficient of the small model as non-interference data to obtain the blocking interference factor value under the current test state.
Blockage stem of ith point of large-scale modelDisturbance factor epsiloniComprises the following steps:
Figure BDA0002850527980000051
in the formula, CP2,iIn order to select the pressure coefficient corresponding to the ith point at the same position as the small scale model from the pressure coefficients of the large scale model in the nominal mach number state, the subscript P2 represents the large scale model.
The blocking interference factor epsilon of the large-scale model in the current test state is as follows:
Figure BDA0002850527980000052
the different scaling ratios mean that the shapes of the two models are similar in geometry, but the proportions are different, the maximum sectional area of the small model is not more than 0.3% of the sectional area of the test section, and the sectional area of the large model is not more than 1.0% of the sectional area of the test section;
the pressure coefficient refers to the characteristic quantity of the surface pressure of the model, and the static pressure and the quick pressure of the incoming flow of the test section are adopted for carrying out non-dimensionalization;
the nominal Mach number is a corresponding target Mach number which is obtained by ignoring flow field fluctuation caused by factors such as wind tunnel control and model disturbance influence under an ideal condition;
the small disturbance equation is a control equation approximately satisfied by flow under the assumption of no sticking and no rotation;
the pressure coefficient difference refers to the difference between the pressure coefficient of the surface measuring point of the small-scale model and the pressure coefficient of the surface measuring point of the large-scale model;
the blocking interference factor refers to a dimensionless coefficient related to the shape, the volume, the wall plate parameters, the wind tunnel operation conditions and the like of the test model, and the value of the dimensionless coefficient is used for calculating the correction quantity of the Mach number at the inlet of the test section.
In order to achieve a better technical effect, the Mach numbers of the two sets of scaling models to be compared need to be interpolated to obtain a test result under the nominal Mach number;
in order to achieve a better technical effect and accurately obtain the independent influence quantity of the blocking interference, the compared pressure coefficient of the measuring point must be insensitive to the attitude angle of the model so as to eliminate the influence of the difference of the attack angle caused by the scale of the model;
in order to achieve a better technical effect, the pressure coefficients of the three measuring points are compared to respectively determine the blocking interference factors, and then the three values are averaged to be used as the blocking interference factors of the model under the test condition.
The technical solution of the present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
The embodiment 1 of the invention provides a method for obtaining a blocking interference factor of a transonic wind tunnel, in particular to a method for obtaining a blocking interference factor of a 2.4-meter transonic wind tunnel hole wall test section, wherein the appearance of a pressure measurement model refers to the structure of an American X-37B aerospace plane, machine head pressure measurement tests of two models with different scaling ratios of 1:10 and 1:4.5 are carried out in the 2.4-meter transonic wind tunnel hole wall test section, the appearance of the models is contrasted to be shown in figure 1, and measuring points are symmetrically distributed on the left side and the right side of a machine head.
The working process is as follows:
(1) through a Mach number fixed variable attack angle test, a change curve of the pressure coefficient of a measuring point at the head of the model along with the attack angle is obtained, as shown in FIG. 2; the pressure coefficients of the measuring points are marked under four different attack angles of the small-scale model, and four curves from top to bottom respectively correspond to the attack angles of 0.13 degrees, 4.24 degrees, 8.35 degrees and 10.43 degrees. The horizontal axis index of the coordinate system is 17 marked measuring points of the head of the small-scale model, and the vertical axis is a pressure coefficient.
(2) Interpolating the Mach number by the pressure coefficient of the selected measuring point to obtain the pressure coefficient under the nominal Mach number, and comparing the pressure coefficients before and after interpolation, as shown in FIG. 3; the difference between the actual Mach number and the nominal Mach number under each attack angle is 0.0002-0.0012, the difference between the pressure coefficients before and after interpolation is 0.0003-0.0030, and the maximum value appears at the attack angle of 4.24 degrees.
(3) According to the test results, three measuring points with small pressure coefficient change along with the attack angle are determined, in the example, 9 th, 10 th and 11 th points are selected, and the results of the example are shown in the following table;
Figure BDA0002850527980000061
(4) checking whether the root mean square deviation of the pressure coefficients at the four attack angles is less than 0.0100, wherein the calculation results of the example are 0.0087, 0.0076 and 0.0090 respectively, and the calculation requirements are met;
(5) pressure coefficient difference delta C of measuring points at the same position of two sets of models when attack angle 0 is obtainedPThe results were 0.0029, 0.0036 and 0.0036, respectively;
(6) according to the pressure coefficient difference deltaCPSolving the blocking interference factors corresponding to the three measuring points as 0.0014, 0.0017 and 0.0016 respectively according to the functional relation between the blocking interference factors and the blocking interference factor epsilon;
(7) and calculating the average value of the three measuring points as a blockage interference factor of the large-scale model in the current test state, wherein the quantity value is 0.0016.
And (3) obtaining a blockage interference factor according to the steps, and then carrying out blockage interference correction on the large-scale model test result, wherein according to the calculation result, the corrected test section inlet Mach number is about 0.8014, namely the blockage interference causes the acceleration of the model bypass flow, and the magnitude value is about 0.0014.
The method of the invention obtains the blocking interference factor of the specific test equipment through different scaling model tests on the basis of accuracy and reliability, so as to be beneficial to the correction and analysis of the blocking interference amount and provide a powerful means for the design of the wind tunnel wall plate and the correlation analysis of test data.
Finally, it should be noted that the above embodiments are only used for illustrating the technical solutions of the present invention and are not limited. Although the present invention has been described in detail with reference to the embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.

Claims (3)

1. A method for obtaining a blocking interference factor of a transonic wind tunnel is realized based on a large-scale model and a small-scale model which have the same appearance and different scaling ratios, and comprises the following steps:
respectively marking measuring points at a plurality of same positions of the large-scale model and the small-scale model;
respectively carrying out a constant Mach number variable attack angle pressure measurement test on the large-scale model and the small-scale model after the measurement points are marked in the wind tunnel to obtain pressure coefficients of the marked measurement points of the two sets of scale models under different attack angles;
performing Mach number interpolation on the pressure coefficient of each set of model to obtain the pressure coefficient in a nominal Mach number state;
selecting k points with the minimum pressure coefficient changing along with the attack angle from the pressure coefficients under the nominal Mach number state of the small scale model, wherein k is not less than 3;
selecting k points at the same position as the small scale model from the pressure coefficients of the large scale model in the nominal Mach number state, and calculating the differential quantity of the pressure coefficients of the k points corresponding to the large scale model and the small scale model;
obtaining k blockage interference factors according to the difference of the pressure coefficients by combining a small disturbance equation, and solving an average value to obtain the blockage interference factors of the large-scale model in the current test state;
calculating the difference of the pressure coefficients of the k points corresponding to the large-scale model and the small-scale model; the method specifically comprises the following steps:
calculating the differential quantity delta C of the pressure coefficients of the k points corresponding to the large-scale model and the small-scale modelP,iComprises the following steps:
ΔCP,i＝CP1,i-CP2,i，i＝1,2,…,k
wherein, CP1,iIn order to select the pressure coefficient corresponding to the ith point with the minimum pressure coefficient changing along with the attack angle from the pressure coefficients under the nominal Mach number state of the small scale model, the subscript P1 represents the small scale model, CP2,iIn order to select the pressure coefficient corresponding to the ith point at the same position as the small scale model from the pressure coefficients of the large scale model in the nominal mach number state, the subscript P2 represents the large scale model.
2. The method for obtaining the blocking interference factor of the transonic wind tunnel according to claim 1, wherein the maximum sectional area of the small-scale model is not more than 0.3% of the sectional area of the test section, and the sectional area of the large-scale model is not more than 1.0% of the sectional area of the test section.
3. The method for obtaining the blocking interference factor of the transonic wind tunnel according to claim 2, wherein the method is characterized in that k blocking interference factors are obtained according to the difference of the pressure coefficients by combining a small disturbance equation, and an average value is obtained to obtain the blocking interference factor of the large-scale model in the current test state; the method specifically comprises the following steps:
according to the difference Delta C of the pressure coefficient by combining a small disturbance equationP,iObtaining the blockage interference factor epsilon of the ith point of the large-scale modeliComprises the following steps:
Figure FDA0003087047420000021
wherein Ma is a nominal Mach number;
the blocking interference factor epsilon of the large-scale model in the current test state is as follows:
Figure FDA0003087047420000022
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