CN115183978A - Method for measuring transition information of surface boundary layer of large-size thin-wall model - Google Patents
Method for measuring transition information of surface boundary layer of large-size thin-wall model Download PDFInfo
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- CN115183978A CN115183978A CN202210617875.0A CN202210617875A CN115183978A CN 115183978 A CN115183978 A CN 115183978A CN 202210617875 A CN202210617875 A CN 202210617875A CN 115183978 A CN115183978 A CN 115183978A
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- 230000007704 transition Effects 0.000 title claims abstract description 36
- 238000000034 method Methods 0.000 title claims abstract description 29
- 239000011248 coating agent Substances 0.000 claims abstract description 25
- 238000000576 coating method Methods 0.000 claims abstract description 25
- 238000005259 measurement Methods 0.000 claims abstract description 19
- 238000009413 insulation Methods 0.000 claims abstract description 16
- 239000002184 metal Substances 0.000 claims abstract description 11
- 238000012360 testing method Methods 0.000 claims description 21
- 238000012545 processing Methods 0.000 claims description 10
- 239000007769 metal material Substances 0.000 claims description 5
- 238000005507 spraying Methods 0.000 claims description 5
- 238000003780 insertion Methods 0.000 claims description 4
- 230000037431 insertion Effects 0.000 claims description 4
- 229910052755 nonmetal Inorganic materials 0.000 claims description 4
- 238000004441 surface measurement Methods 0.000 claims description 2
- 238000005516 engineering process Methods 0.000 description 7
- 238000003754 machining Methods 0.000 description 3
- 238000005524 ceramic coating Methods 0.000 description 2
- 239000004973 liquid crystal related substance Substances 0.000 description 2
- 238000004458 analytical method Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 238000001931 thermography Methods 0.000 description 1
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
- G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
- G01J5/48—Thermography; Techniques using wholly visual means
- G01J5/485—Temperature profile
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/08—Aerodynamic models
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- Spectroscopy & Molecular Physics (AREA)
- Investigating Or Analyzing Materials Using Thermal Means (AREA)
Abstract
The invention discloses a method for measuring transition information of a surface boundary layer of a large-size thin-wall model, wherein the thin-wall model is processed by adopting high-strength metal, the overall dimension of a measurement region on the surface of the model is processed according to negative tolerance, a high-emissivity heat insulation coating is sprayed on the surface of the model, the model is quickly inserted into a flow field after the flow field is established and stabilized in a hypersonic wind tunnel running for a long time, the surface temperature distribution of the model is observed in real time by adopting an infrared thermal imager, and the transition position and the transition form of the surface boundary layer of the model are judged through the temperature distribution.
Description
Technical Field
The invention relates to a method for measuring transition information of a surface boundary layer of a large-size thin-wall model, and belongs to the field of wind tunnel test measurement.
Background
In hypersonic wind tunnels, a temperature-sensitive coating technology, a liquid crystal friction measurement technology or an infrared thermal map technology and other non-contact surface measurement technologies are generally adopted to display and measure transition of a model surface boundary layer. The temperature-sensitive coating technology or the liquid crystal friction resistance measurement technology needs to spray a sensitive coating material on the surface of the model, and the test process is complex and the test efficiency is low. The infrared thermography technology does not need a sensitive coating, but is generally suitable for processing a model made of a non-metal material with high emissivity and low heat conductivity, but the strength of the non-metal material cannot meet the test requirement of a large-size thin-wall model.
Disclosure of Invention
The technical problem to be solved by the invention is as follows: the method overcomes the defects of the prior art, provides the information measuring method for transition of the surface boundary layer of the large-size thin-wall model, and solves the problem of transition measurement of the surface boundary layer of the large-size thin-wall model.
The technical solution of the invention is as follows:
a method for measuring transition information of a surface boundary layer of a large-size thin-wall model comprises
The thin-wall model is made of high-strength metal, and the outline dimension of a measurement region on the surface of the model is processed according to negative tolerance;
spraying a heat insulation coating with the emissivity larger than 0.9 on a measurement area of the surface of the model, namely a negative tolerance processing area, wherein the processing negative tolerance value is the same as the thickness of the heat insulation coating, and the heat insulation coating is made of a non-metal material;
in a hypersonic wind tunnel running for a long time, after a wind tunnel flow field is established and stabilized, a model is quickly inserted into the flow field, the surface temperature distribution of the model is measured in real time by adopting a thermal infrared imager, and the position and the form of transition of a boundary layer are determined according to the temperature distribution.
Preferably, the minimum wall thickness of the model is less than 1mm, and the ratio of the maximum projection area of the model to the average wall thickness is more than 500mm.
Preferably, the strength of the metal for thin-wall mold machining is not less than 30CrMnSiA, and the rigidity of the metal for thin-wall mold machining is not less than 30CrMnSiA.
Preferably, the measurement area of the surface of the model is machined with negative tolerances, and the other dimensions of the model are machined to standard tolerances.
Preferably, the external dimension of the model surface sprayed with the thermal insulation coating is consistent with the ideal external shape.
Preferably, the surface temperature of the model before the test is room temperature, and the temperature distribution is uniform and consistent.
Preferably, the attitude angle of the model is kept constant during the insertion of the model into the flow field.
Preferably, in the process of inserting the model into the flow field, the running path of the model is parallel to the observation path of the thermal infrared imager.
Preferably, the acquisition frequency of the thermal infrared imager is not less than 100Hz.
Preferably, the thermal infrared imager completely records the surface temperature distribution change of the model in the process of inserting into the flow field.
Compared with the prior art, the invention has the advantages that:
(1) According to the invention, the large-size thin-wall model is processed by adopting a high-strength metal material, so that the strength of the model is ensured, and the requirements of a wind tunnel test are met;
(2) The surface of the model is sprayed with the high-emissivity heat-insulating coating, so that the requirement of high-precision measurement of the temperature distribution of the surface of the model is met;
(3) The contour dimension of the model measuring area is processed according to the negative tolerance, and the thickness of the coating on the surface of the model is basically consistent with the value of the negative tolerance, so that the contour dimension precision of the model is ensured.
(4) The method for measuring the transition information of the model surface boundary layer is used for measuring the transition information of the model surface boundary layer in the conventional hypersonic wind tunnel by adopting a method of fast inserting the model and measuring the temperature distribution of the model surface in real time by the thermal infrared imager, and has the advantages of simple operation and high test efficiency.
Drawings
FIG. 1 is a schematic view of the model structure of the present invention;
FIG. 2 is a schematic view of a wind tunnel test arrangement of the present invention.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings.
The invention adopts high-strength metal to process a thin-wall model, the overall dimension of a model measuring area is processed according to negative tolerance, a heat insulation coating with high emissivity is sprayed on the surface of the measuring area, and the value of the negative tolerance is equivalent to the thickness of the heat insulation coating. In a conventional hypersonic wind tunnel which runs for a long time, after a wind tunnel flow field is established and stabilized, a model is quickly inserted into the flow field, the surface temperature distribution of the model is measured in real time by adopting a thermal infrared imager, and the transition information of a boundary layer is obtained through the surface temperature distribution of the model.
The method comprises the following specific steps:
(1) As shown in fig. 1, a large-size thin-wall model is first machined by using high-strength metal, the outline dimension of a measurement region of the model is machined according to a negative tolerance, and the other dimensions of the model are machined according to a standard tolerance. The minimum wall thickness of the model is less than 1mm, and the strength and the rigidity of the metal for processing the thin-wall model are not less than 30CrMnSiA.
(2) And spraying a high-emissivity heat insulation coating in the model measurement area, wherein the thickness of the heat insulation coating is basically consistent with the numerical value of the negative tolerance of model machining. The external dimension of the model surface sprayed with the heat insulation coating is consistent with the ideal external dimension.
(3) In a conventional hypersonic wind tunnel with the wind tunnel running time being more than 10s, before the test, the model is arranged outside the flow field, after the wind tunnel flow field is established and stabilized, the model is quickly inserted into the flow field, and the thermal infrared imager is adopted to measure the surface temperature distribution of the model in real time. The acquisition frequency of the thermal infrared imager is not less than 100Hz.
(4) And judging the position and the form of transition of the surface boundary layer of the model through the analysis of the temperature distribution of the surface of the model.
In the wind tunnel test, the model and the measuring instrument are arranged as shown in fig. 2, the model enters a flow field from bottom to top, and the thermal infrared imager shoots the surface temperature distribution of the model at the top of the test section. In a conventional hypersonic wind tunnel with the operation time reaching the order of seconds, a model is initially arranged outside a flow field, after the wind tunnel flow field is established and stabilized, a test model is quickly inserted into the flow field, the thermal infrared imager is adopted to completely record the surface temperature distribution information of the model in the process of inserting the model into the flow field, and the model insertion flow field path is parallel to the thermal infrared imager shooting path. And sending the information obtained by the thermal infrared imager to a computer, selecting the temperature distribution of the surface of the model just inserted into the flow field on the computer, and judging the transition position and the transition form of the boundary layer on the surface of the model by comprehensively considering the appearance characteristics and the aerodynamic knowledge of the surface of the model.
Aiming at the measurement requirement of the boundary layer transition test of the large-size thin-wall model, the invention aims at the maximum projection area S (unit mm) of the thin-wall model 2 ) The ratio S/b to the average wall thickness b (in mm) is greater than 500mm. Processing a large-size thin-wall model by using high-strength metal so as to ensure the strength and rigidity of the test model; spraying a high-emissivity heat insulation coating on the surface of the model to meet the measurement requirement of a thermal infrared imager; the model is processed by adopting negative tolerance, and the value of the negative tolerance is equal to the thickness of the coating so as to ensure the overall dimension of the sprayed model; and judging transition information of the surface boundary layer by using the measured temperature distribution of the model surface.
The invention solves the difficult problem of transition measurement of the boundary layer of the large-size thin-wall model, ensures the appearance of the model by adopting a method of spraying the coating on the surface of the model with negative tolerance, combines the measurement of the thermal insulation coating with high emissivity with the thermal infrared imager, and has the advantages of simple operation and high test efficiency.
Example 1
In a transition measurement test of the airfoil model, the thickness of the airfoil model is less than 5mm, the length is 380mm, the width is 120mm, the appearance processing tolerance of the surface of the model is (-10 to-20 mu m), the ceramic coating is sprayed on the surface of the model, and the thickness of the ceramic coating is about 10 to 20 mu m, so that the appearance size tolerance of the model after the coating is sprayed is guaranteed to be-10 to 10 mu m.
The method comprises the steps that a transition measurement test of an opening boundary layer in a conventional hypersonic wind tunnel is conducted, the test Mach number is 6, the wind tunnel operation time is larger than 30s, a wing surface model is arranged on the south side in a test section in the process of establishing a wind tunnel flow field, an infrared thermal imager shoots a test section south-side window from south to north, after the wind tunnel flow field is established and stabilized, the model is quickly inserted into the flow field from south to north, the insertion time is about 0.15s, the collection frequency of the infrared thermal imager is 100Hz, the collected model surface temperature distribution is analyzed when the model just reaches the center of the flow field, and the transition position and the form of the wing surface boundary layer of the wing surface model are judged. And boundary layer transition position and transition form information of the large-size thin-wall airfoil under different attack angle conditions is obtained.
Those skilled in the art will appreciate that those matters not described in detail in the present specification are well known in the art.
Claims (10)
1. A method for measuring transition information of a surface boundary layer of a large-size thin-wall model is characterized by comprising the following steps: comprises that
The thin-wall model is made of high-strength metal, and the outline dimension of a measurement area on the surface of the model is processed according to negative tolerance;
spraying a heat insulation coating with the emissivity larger than 0.9 on a measurement area of the surface of the model, namely a negative tolerance processing area, wherein the processing negative tolerance value is the same as the thickness of the heat insulation coating, and the heat insulation coating is made of a non-metal material;
in a hypersonic wind tunnel running for a long time, after a wind tunnel flow field is established and stabilized, a model is quickly inserted into the flow field, the surface temperature distribution of the model is measured in real time by adopting a thermal infrared imager, and the position and the form of transition of a boundary layer are determined according to the temperature distribution.
2. The method for measuring transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the minimum wall thickness of the model is less than 1mm, and the ratio of the maximum projection area of the model to the average wall thickness is greater than 500mm.
3. The method for measuring transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the strength of the metal for thin-wall model processing is not less than 30CrMnSiA, and the rigidity of the metal for thin-wall model processing is not less than 30CrMnSiA.
4. The method for measuring transition information of the surface boundary layer of the large-size thin-wall model of claim 1, wherein the model surface measurement region is processed with a negative tolerance, and other dimensions of the model are processed with a standard tolerance.
5. The method for measuring the transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the external dimension of the model surface sprayed with the thermal insulation coating is consistent with the ideal external shape.
6. The method for measuring transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the surface temperature of the model before the test is room temperature, and the temperature distribution is uniform and consistent.
7. The method for measuring transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the attitude angle of the model is kept unchanged during the process of inserting the model into the flow field.
8. The method for measuring transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 7, wherein a running path of the model is parallel to an observation path of the thermal infrared imager when the model is inserted into the flow field.
9. The method for measuring the transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the collection frequency of the thermal infrared imager is not less than 100Hz.
10. The method for measuring the transition information of the surface boundary layer of the large-size thin-wall model as claimed in claim 1, wherein the thermal infrared imager completely records the surface temperature distribution change during the insertion of the model into the flow field.
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| CN202210617875.0A CN115183978A (en) | 2022-06-01 | 2022-06-01 | Method for measuring transition information of surface boundary layer of large-size thin-wall model |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111832159A (en) * | 2020-06-23 | 2020-10-27 | 北京临近空间飞行器系统工程研究所 | Flight test data-based boundary layer transition array surface dynamic evolution process determination method |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4774835A (en) * | 1986-11-13 | 1988-10-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method for laminar boundary layer transition visualization in flight |
| CN108318214A (en) * | 2018-01-02 | 2018-07-24 | 中国航天空气动力技术研究院 | A kind of metal pattern surface fluidised form method for fast measuring |
| CN111498083A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Laminar flow wing aircraft aerodynamic outer edge tolerance control method |
| CN112304563A (en) * | 2020-10-30 | 2021-02-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test method for researching influence of transition on aerodynamic characteristics of hypersonic aircraft |
| CN114216645A (en) * | 2022-02-21 | 2022-03-22 | 中国航空工业集团公司沈阳空气动力研究所 | Hypersonic velocity boundary layer transition flow control test device and method |
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- 2022-06-01 CN CN202210617875.0A patent/CN115183978A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4774835A (en) * | 1986-11-13 | 1988-10-04 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Method for laminar boundary layer transition visualization in flight |
| CN108318214A (en) * | 2018-01-02 | 2018-07-24 | 中国航天空气动力技术研究院 | A kind of metal pattern surface fluidised form method for fast measuring |
| CN111498083A (en) * | 2020-04-15 | 2020-08-07 | 成都飞机工业（集团）有限责任公司 | Laminar flow wing aircraft aerodynamic outer edge tolerance control method |
| CN112304563A (en) * | 2020-10-30 | 2021-02-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel test method for researching influence of transition on aerodynamic characteristics of hypersonic aircraft |
| CN114216645A (en) * | 2022-02-21 | 2022-03-22 | 中国航空工业集团公司沈阳空气动力研究所 | Hypersonic velocity boundary layer transition flow control test device and method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111832159A (en) * | 2020-06-23 | 2020-10-27 | 北京临近空间飞行器系统工程研究所 | Flight test data-based boundary layer transition array surface dynamic evolution process determination method |
| CN111832159B (en) * | 2020-06-23 | 2023-08-29 | 北京临近空间飞行器系统工程研究所 | Method for determining boundary layer transition array plane dynamic evolution process based on flight test data |
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