CN116929703A - Low-temperature wind tunnel Mach number determination method considering blocking effect and application thereof - Google Patents
Low-temperature wind tunnel Mach number determination method considering blocking effect and application thereof Download PDFInfo
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Abstract
The application discloses a method for determining Mach number of a low-temperature wind tunnel considering a blocking effect and application thereof, and aims to solve the defect that when a model exists in a transonic wind tunnel, the Mach number corresponding to model bypass is higher due to the constraint of a wallboard on the model and a support system bypass field, and the modified Mach number deviates from a nominal value due to the traditional method. According to the application, the blocking effect of the test model and the supporting system is considered as the increment of the control target Mach number, after the total pressure and the total temperature of wind tunnel operation and the nominal Mach number are defined, the Mach number increment caused by the reference position Mach number correction quantity and the blocking effect is calculated by using the wind tunnel reference position Mach number corresponding relation and the blocking effect correction factor, and the model bypass equivalent Mach number is ensured to be equal to the nominal value through superposition before the test, so that the reliability of the test result is improved. By adopting the application, the corrected data can be ensured to be subjected to comparison analysis under the same Mach number, and the data quality is obviously improved.
Description
Technical Field
The application relates to the field of experimental aerodynamics, in particular to a method for determining Mach number of a low-temperature wind tunnel by considering a blocking effect and application thereof.
Background
Mach number is the most important simulation parameter in high-speed wind tunnel test, and represents the influence of fluid compressibility, and is defined as the ratio of speed to sound velocity. In a transonic wind tunnel test, the total pressure of a stable section and the static pressure of a reference position are usually measured, then calculated through an isentropic formula, a control target Mach number is set before operation, and the wind tunnel Mach number control is realized by combining the corresponding relation between the average Mach number of a model area of a test section obtained through flow field calibration and the Mach number of the reference position. In practice, due to the existence of the test model and the wall plate of the test section, the corresponding relation obtained by the flow correction can only ensure the flow field Mach number of the air tunnel model area; when the model exists, the constraint of the wall plates on the model and the support system around the flow field generally causes the Mach number corresponding to the model around flow to be higher, the reliability of the test result is affected, and an equivalent model around flow Mach number is obtained by a method for correcting the hole wall interference in the test. By adopting the mode, on one hand, the additional error and the test cost caused by the interference correction of the cavity wall are increased; on the other hand, the corrected test results are not target values required by the aircraft design, and cause great trouble to data evaluation and later use. Especially for low-temperature wind tunnels, wall boundary conditions are changed due to different operating temperatures, and the Mach number correction amounts are inconsistent, so that the difficulty of data analysis and comparison is greatly increased.
To this end, a new apparatus and/or method is urgently needed to solve the above-mentioned problems.
Disclosure of Invention
The application aims at: aiming at the defect that when a model exists in a transonic wind tunnel, the Mach number corresponding to model bypass is higher due to the constraint of a wallboard on the model and a support system bypass field, and the modified Mach number deviates from a nominal value due to the traditional method, the low-temperature wind tunnel Mach number determining method considering the blocking effect is provided. More specifically, the application provides a method for determining the Mach number of a wind tunnel reference position control target in consideration of a blocking effect, which is particularly suitable for a low-temperature wind tunnel test, and provides a powerful means for data evaluation and correlation analysis on the basis of accurately and reliably determining the wind tunnel operation condition.
In order to achieve the above purpose, the present application adopts the following technical scheme:
a method for determining Mach number of low-temperature wind tunnel by considering blocking effect comprises the following steps:
s1, aiming at the total pressure and total temperature state of test operation, calibrating and testing the obtained nominal Mach number by using an air wind tunnel flow fieldMMach number from reference positionM ref Corresponding relation, calculating the Mach number correction delta of the reference position under the test running stateM ref The calculation formula is as follows:
（1）；
s2, correcting factor by using blocking effectf(M,Ret) And calculating the equivalent Mach number increment caused by the test model, wherein the calculation formula is as follows:
（2），
in the method, in the process of the application,is Reynolds number (Reynolds number)>Is an equivalent mach number increment;
s3, utilizing the model volumeV m Volume of support systemV s Volume of test model used in correction and calibration of blocking effectV mref Test support system volume adopted in correction and calibration of blocking effectV sref Calculating the increment delta of the bypass flow equivalent Mach number caused by the total blocking effectM t The calculation formula is as follows:
（3）；
s4, from the nominal Mach numberMDeducting the Mach number correction of the reference positionM ref Wrap-around equivalent Mach number delta due to total blocking effectM t Determining the Mach number of the control target of the reference position under the current total temperature and total pressure stateM cref The calculation formula is as follows:
（4）。
in the step S1, flow field calibration is to measure static pressure distribution on a central line of a transonic wind tunnel test section by using a static pressure detection tube, and calculate and obtain Mach number distribution in the test section by combining total pressure measured by a wind tunnel stable section.
The Mach number at the reference position is calculated by utilizing static pressure measured at a side wall of a transonic wind tunnel test section or a certain position in a wind tunnel residence chamber and combining total pressure measured by a wind tunnel stabilizing section, and is a direct control target of the Mach number of the wind tunnel in the test.
In the step S1, the corresponding relation refers to the relation between the average Mach number of the model area of the test section and the Mach number of the reference position, which is obtained through flow field calibration, a curve is drawn by using a test result, the abscissa is the nominal Mach number, the ordinate is the difference between the average Mach number and the nominal Mach number, and then the correction quantity of the Mach number of the reference position in the current running state is obtained by using a fitting or interpolation method.
The blocking effect is that the model bypass flow in the test section is different from the actual flight state due to the existence of the test model and the supporting system, and the model bypass flow is corrected by adopting a mode of overlapping Mach number increment.
The blocking effect correction factor is Mach number increment caused by blocking effect, is a function of test Mach number and Reynolds number, and is determined by performing a special standard mode contrast test on the transonic wind tunnel, and is an input condition for evaluating and correcting test results. Occlusion effect correction factorf(M,Ret) For the calculation of (a), reference can be made to: liu Guangyuan, wei Zhi, peng Xin, chen Dehua, gu Zhiliang application of transonic wind tunnel slot wall disturbance assessment and correction techniques [ J]Aviation journal, 2018, 039 (002): 73-82. And S2, performing polynomial fitting on the flow field calibration result and the blocking effect correction factor, and interpolating at the wind tunnel operation parameter to obtain a corresponding correction value, so that a better technical effect can be obtained.
The method is applied to transonic wind tunnel Mach number determination.
Aiming at the problem that when a model exists in a transonic wind tunnel, the Mach number corresponding to model bypass is higher due to the constraint of a wallboard on the model and a support system bypass field, the test result corrected by the conventional tunnel wall interference correction method is not a target value required by aircraft design, and the problem that data evaluation and later use are greatly plagued is solved.
In order to achieve a better technical effect, after the fresh air tunnel flow field is debugged, before the model is applied, testing work of the blocking effect correction factor is carried out, and the change relation of the blocking effect correction factor along with test parameters (Mach number and Reynolds number) is obtained by using standard model test results before and after the interference of the corrected tunnel wall.
In order to achieve better technical effects, it is proposed in flow field calibration to mount the static pressure probe on the most commonly used support system, taking the blocking effect of the support system into account as the reference position Mach number correction.
In the application, the blocking effect of the test model and the supporting system is considered as the increment of the control target Mach number, after the total pressure and the total temperature of the wind tunnel operation are defined, the Mach number increment caused by the blocking effect is calculated by using the Mach number corresponding relation of the wind tunnel reference position and the blocking effect correction factor, and the model bypass equivalent Mach number is ensured to be equal to the nominal value by superposition before the test, so that the reliability of the test result is improved.
The application provides a new thought for determining the Mach number of a low-temperature wind tunnel, which utilizes a blocking effect correction factor to calculate Mach number increment under different running conditions of the wind tunnel, and before the wind tunnel runs, the correction and a reference position Mach number correction are overlapped on a nominal Mach number together to obtain a control target Mach number of a reference position. The application can ensure that the Mach number after data correction is the nominal Mach number required by the aircraft design, is particularly suitable for low-temperature wind tunnels, superimposes the corresponding corrected Mach numbers under different operating temperature conditions, can ensure that the corrected data is subjected to comparison analysis under the same Mach number, and obviously improves the data quality.
In summary, due to the adoption of the technical scheme, the application has the following beneficial effects:
(1) The application provides a new thought for determining the Mach number of a low-temperature wind tunnel, breaks through the original path for calculating the Mach number, and superimposes the blocking effect of a model and a supporting system in Mach number increment so that the Mach number after the blocking effect is corrected is a target value required by an aircraft design unit, and belongs to innovation of control thought;
(2) Before the test, the control target Mach number is rapidly determined according to the existing data, so that the corrected data can meet the model development requirements, the method is suitable for low-temperature and conventional wind tunnels, is particularly suitable for transonic wind tunnel Mach number determination, has the advantage of high engineering practicability, and further improves the accuracy of Mach number determination results.
Drawings
In addition to the foregoing, the present application has other objects, features and advantages. The present application will be described in further detail with reference to the drawings. Wherein:
FIG. 1 is a graph of Mach number correspondence for a reference position of a low temperature wind tunnel.
FIG. 2 is a graph of a correction factor for the plugging effect of a low temperature wind tunnel.
Detailed Description
All of the features disclosed in this specification, or all of the steps in a method or process disclosed, may be combined in any combination, except for mutually exclusive features and/or steps.
Any feature disclosed in this specification may be replaced by alternative features serving the same or equivalent purpose, unless expressly stated otherwise. That is, each feature is one example only of a generic series of equivalent or similar features, unless expressly stated otherwise.
Example 1
The flow field calibration and the blockage effect correction factor calibration of the empty wind tunnel are completed for a certain low-temperature wind tunnel, the corresponding relation of the Mach number of the reference position determined by the flow field calibration is shown in figure 1, and the Mach number correction of the reference position is only a function of the test Mach number and does not change along with the Reynolds number; the plugging effect correction factor is shown in fig. 2, and changes significantly with the test mach number and reynolds number. A model wind tunnel test of a certain conveyor is required, and wind tunnel operation parameters are shown in table 1.
The test model has the volume ofV m =0.0381m 3 The volume of the supporting system isV s =0.0285m 3 The volume of the test model adopted in correction and calibration of the blocking effect is as followsV mref =0.0356m 3 The volume of the supporting system isV sref =0.0232m 3 . In order to ensure that the Mach number after the blockage effect correction is equal to the target value in the table 1, the method provided by the application needs to be adopted to determine the wind tunnel control target Mach number.
TABLE 1 Low temperature wind tunnel test status table for a transport model
For this example, the operational flow is as follows.
(1) With reference to fig. 1, the reference position mach number correction amount Δmref corresponding to each test state in table 1 is obtained as follows.
The data of fig. 1 were fitted with 6 th degree polynomials, the fitting formula being as follows.
According to the fitting result, calculating the Mach number correction amount delta of the reference position of each test state in table 1M ref The results are shown in Table 2.
Table 2 reference Mach number modifier
(2) Using fig. 2, the wrap-around equivalent mach number delta from the blocking effect corresponding to each test state in table 1 was calculatedM t 。
For each run reynolds number data in fig. 2, 6 th order polynomial fits are performed, with the fitting coefficients shown in table 3.
TABLE 3 fitting coefficient table for occlusion effect correction factors
The mach numbers were first interpolated to obtain the equivalent mach number increments corresponding to each test state at the same reynolds number, and the results are shown in table 4.
TABLE 4 Mach number delta table for blocking effect for different Reynolds number models
Then interpolating the Reynolds number to obtain equivalent Mach number increment father corresponding to each test stateM m 。
TABLE 5 Reynolds number model plug effect Mach number increment table for test
(3) With reference to FIG. 2, the model corresponding to each test state in Table 1 was calculated, as was the wrap-around equivalent Mach number delta due to the effect of support system blockageM t The calculation formula is shown as the following formula (3):
（3）。
the results are shown in Table 6.
Table 6 wind tunnel control Mach number scale value table under test condition
(4) The Mach number of the target is subtracted from the Mach number correction of the reference position and the Mach number increment of the blocking effect is obtained to obtain the control target Mach number under the test operation condition, and the control target Mach number is shown in a table 6.
Obtaining the low-temperature wind tunnel control target Mach number considering the blocking effect according to the steps, and according to the calculation result, the Mach numbers corresponding to different total temperatures and total pressures are different,Ret=1.00E+07，Mwhen=0.785, the control target mach number is 0.78519.
The above description is only one embodiment of the present application and is not intended to limit the present application, and various modifications and variations of the present application will be apparent to those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the principle of the present application should be included in the protection scope of the present application.
Claims (7)
1. The method for determining the Mach number of the low-temperature wind tunnel by considering the blocking effect is characterized by comprising the following steps of:
s1, aiming at the total pressure and total temperature state of test operation, calibrating and testing the obtained nominal Mach number by using an air wind tunnel flow fieldMMach number from reference positionM ref Corresponding relation, calculating the Mach number correction delta of the reference position under the test running stateM ref The calculation formula is as follows:
（1）；
s2, correcting factor by using blocking effectf(M,Ret) And calculating the equivalent Mach number increment caused by the test model, wherein the calculation formula is as follows:
（2），
in the method, in the process of the application,is Reynolds number (Reynolds number)>Is an equivalent mach number increment;
s3, utilizing the model volumeV m Volume of support systemV s Volume of test model used in correction and calibration of blocking effectV mref Test support system volume adopted in correction and calibration of blocking effectV sref Calculating the increment delta of the bypass flow equivalent Mach number caused by the total blocking effectM t The calculation formula is as follows:
（3）；
s4, from the nominal Mach numberMDeducting the Mach number correction of the reference positionM ref Wrap-around equivalent Mach number delta due to total blocking effectM t Determining the Mach number of the control target of the reference position under the current total temperature and total pressure stateM cref The calculation formula is as follows:
（4）。
2. the method for determining mach number of low-temperature wind tunnel according to claim 1, wherein in S1, flow field calibration means that static pressure distribution on a central line of a transonic wind tunnel test section is measured by using a static pressure detecting tube, and mach number distribution in the test section is obtained by combining total pressure calculation measured by a wind tunnel stabilizing section.
3. The method for determining the Mach number of the low-temperature wind tunnel considering the blocking effect according to claim 1, wherein the Mach number of the reference position is a Mach number obtained by calculating the total pressure measured by utilizing the static pressure measured by the side wall of a transonic wind tunnel test section or a certain position in a wind tunnel residence chamber and combining the total pressure measured by the wind tunnel stabilization section, and is a direct control target of the Mach number of the wind tunnel in the test.
4. The method for determining the mach number of the low-temperature wind tunnel according to claim 1, wherein in S1, the corresponding relation refers to the relation between the average mach number of the model area of the test section obtained by flow field calibration and the mach number of the reference position, a curve is drawn by using the test result, the abscissa is the nominal mach number, and the ordinate is the difference between the nominal mach number and the nominal mach number, and then the correction amount of the mach number of the reference position in the current running state is obtained by using a fitting or interpolation method.
5. The method for determining the Mach number of the low-temperature wind tunnel considering the blocking effect according to claim 1, wherein the blocking effect is that the difference between the model bypass flow in the test section and the actual flight state is caused by the existence of the test model and the supporting system, and the blocking effect is corrected by adopting a mode of overlapping Mach number increment.
6. The method for determining the mach number of the low-temperature wind tunnel considering the blocking effect according to claim 1, wherein the blocking effect correction factor refers to a mach number increment caused by the blocking effect, is a function of a test mach number and a reynolds number, and the transonic wind tunnel needs to be subjected to a special standard mode contrast test to determine the blocking effect correction factor, and the blocking effect correction factor is an input condition for evaluating and correcting a test result.
7. The use of a method for determining the mach number of a cryogenic wind tunnel taking into account the effect of plugging according to claim 1, wherein the method is applied to the determination of the mach number of a transonic wind tunnel.
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117129179A (en) * | 2023-10-26 | 2023-11-28 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number correction method for double-support test under continuous wind tunnel wing |
Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006066933A1 (en) * | 2004-12-22 | 2006-06-29 | Airbus Deutschland Gmbh | Method and apparatus for improving the accuracy of wind tunnel measurements in order to correct the influence of a suspension device |
| JP2010243400A (en) * | 2009-04-08 | 2010-10-28 | Japan Aerospace Exploration Agency | Building berth support interference correcting method in subsonic half model wind tunnel test |
| US20140076041A1 (en) * | 2012-09-20 | 2014-03-20 | The Boeing Company | Correction of Pressure Signals Measured During Supersonic Wind Tunnel Testing |
| JP2016004031A (en) * | 2014-06-19 | 2016-01-12 | 株式会社産学連携機構九州 | Wind tunnel test system and wind tunnel test method |
| KR101869648B1 (en) * | 2017-03-23 | 2018-06-21 | 국방과학연구소 | Flow rate calibration device for wind tunnel model and method thereof |
| CN109765026A (en) * | 2019-01-21 | 2019-05-17 | 西北工业大学 | A kind of low speed dynamic test wind tunnel wall interference correction correction method |
| CN112525474A (en) * | 2020-12-22 | 2021-03-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining blocking interference factor of transonic wind tunnel |
| CN112945506A (en) * | 2021-02-03 | 2021-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Sub-transonic static pressure control method suitable for temporary-impulse high-speed wind tunnel |
| CN112945500A (en) * | 2021-02-02 | 2021-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Simulation measurement device and method for influence of blocking degree of transonic wind tunnel |
| CN113029512A (en) * | 2021-04-01 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Air flow field model correction control method for temporary-impulse transonic wind tunnel |
| CN113092051A (en) * | 2021-06-07 | 2021-07-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring system and measuring method for dynamic pressure and flow field distribution of wind tunnel test |
| CN113588199A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Reverse jet flow blockage degree test device and test method for hypersonic wind tunnel |
| CN114018531A (en) * | 2021-11-09 | 2022-02-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test data processing method for hypersonic wind tunnel continuous variable total pressure |
| CN115615655A (en) * | 2022-11-15 | 2023-01-17 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous transonic wind tunnel test data interference correction method |
| CN116519253A (en) * | 2023-03-17 | 2023-08-01 | 北京临近空间飞行器系统工程研究所 | Separation test system and method based on high-Mach number wind tunnel high-blockage test piece |
| CN116519255A (en) * | 2023-03-13 | 2023-08-01 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number accurate control system and method for continuous transonic wind tunnel |
-
2023
- 2023-09-18 CN CN202311196307.9A patent/CN116929703B/en active Active
Patent Citations (16)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2006066933A1 (en) * | 2004-12-22 | 2006-06-29 | Airbus Deutschland Gmbh | Method and apparatus for improving the accuracy of wind tunnel measurements in order to correct the influence of a suspension device |
| JP2010243400A (en) * | 2009-04-08 | 2010-10-28 | Japan Aerospace Exploration Agency | Building berth support interference correcting method in subsonic half model wind tunnel test |
| US20140076041A1 (en) * | 2012-09-20 | 2014-03-20 | The Boeing Company | Correction of Pressure Signals Measured During Supersonic Wind Tunnel Testing |
| JP2016004031A (en) * | 2014-06-19 | 2016-01-12 | 株式会社産学連携機構九州 | Wind tunnel test system and wind tunnel test method |
| KR101869648B1 (en) * | 2017-03-23 | 2018-06-21 | 국방과학연구소 | Flow rate calibration device for wind tunnel model and method thereof |
| CN109765026A (en) * | 2019-01-21 | 2019-05-17 | 西北工业大学 | A kind of low speed dynamic test wind tunnel wall interference correction correction method |
| CN112525474A (en) * | 2020-12-22 | 2021-03-19 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining blocking interference factor of transonic wind tunnel |
| CN112945500A (en) * | 2021-02-02 | 2021-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Simulation measurement device and method for influence of blocking degree of transonic wind tunnel |
| CN112945506A (en) * | 2021-02-03 | 2021-06-11 | 中国空气动力研究与发展中心高速空气动力研究所 | Sub-transonic static pressure control method suitable for temporary-impulse high-speed wind tunnel |
| CN113029512A (en) * | 2021-04-01 | 2021-06-25 | 中国空气动力研究与发展中心高速空气动力研究所 | Air flow field model correction control method for temporary-impulse transonic wind tunnel |
| CN113092051A (en) * | 2021-06-07 | 2021-07-09 | 中国空气动力研究与发展中心低速空气动力研究所 | Measuring system and measuring method for dynamic pressure and flow field distribution of wind tunnel test |
| CN113588199A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Reverse jet flow blockage degree test device and test method for hypersonic wind tunnel |
| CN114018531A (en) * | 2021-11-09 | 2022-02-08 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test data processing method for hypersonic wind tunnel continuous variable total pressure |
| CN115615655A (en) * | 2022-11-15 | 2023-01-17 | 中国航空工业集团公司沈阳空气动力研究所 | Continuous transonic wind tunnel test data interference correction method |
| CN116519255A (en) * | 2023-03-13 | 2023-08-01 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number accurate control system and method for continuous transonic wind tunnel |
| CN116519253A (en) * | 2023-03-17 | 2023-08-01 | 北京临近空间飞行器系统工程研究所 | Separation test system and method based on high-Mach number wind tunnel high-blockage test piece |
Non-Patent Citations (3)
| Title |
|---|
| 刘光远: ""跨声速风洞槽壁干扰评估与修正技术的应用"", 《航空学报》, vol. 39, no. 2, pages 78 - 87 * |
| 杨依峰: ""风洞洞壁干扰数值模拟研究"", 《导弹与航天运载技术》, no. 6, pages 73 - 77 * |
| 程克明: "《一种新型二元风洞侧壁干扰修正方法——当地修正法》", 《空气动力学学报》, no. 3, pages 7 * |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN117129179A (en) * | 2023-10-26 | 2023-11-28 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number correction method for double-support test under continuous wind tunnel wing |
| CN117129179B (en) * | 2023-10-26 | 2023-12-26 | 中国航空工业集团公司沈阳空气动力研究所 | Mach number correction method for double-support test under continuous wind tunnel wing |
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