CN111811769B - Three-dimensional internal rotation type air inlet channel real-time oil flow display method with wave-rider precursor - Google Patents
Three-dimensional internal rotation type air inlet channel real-time oil flow display method with wave-rider precursor Download PDFInfo
- Publication number
- CN111811769B CN111811769B CN202010546271.2A CN202010546271A CN111811769B CN 111811769 B CN111811769 B CN 111811769B CN 202010546271 A CN202010546271 A CN 202010546271A CN 111811769 B CN111811769 B CN 111811769B
- Authority
- CN
- China
- Prior art keywords
- oil
- test
- air inlet
- oil agent
- agent
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
Images
Classifications
-
- 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
- G01M9/065—Measuring arrangements specially adapted for aerodynamic testing dealing with flow
- G01M9/067—Measuring arrangements specially adapted for aerodynamic testing dealing with flow visualisation
Abstract
The invention provides a real-time oil flow display method for an internal rotation type air inlet channel with a waverider in front of a body. Titanium dioxide, silicone oil and oleic acid are adopted for preparing the oil agent, wherein the oleic acid is used for adjusting the viscosity of the oil agent; the oil agent is brushed, namely different oil agents are brushed on different surfaces of the model according to the shearing force of the wall surface, the brushing scheme is favorable for weakening the accumulation of the oil agents, the development of an oil flow pattern is accelerated, and the oil flow stripe trace is clear; the technical scheme of the real-time oil flow test provided by the invention can obtain a high-quality image spectrum of the near-wall surface complex flow of the internal rotation type air inlet channel with the multiplied wave front, avoids the adverse effect of the flow field change in the closing process of the wind tunnel, and can provide a technical scheme for the complex flow analysis of the air inlet channel. The invention also provides a technical scheme of the oil agent adopted by the display method.
Description
Technical Field
The invention belongs to the field of display of a supersonic/hypersonic flow field structure, and particularly relates to the field of display of near-wall flow of a supersonic/hypersonic complex three-dimensional air inlet channel.
Background
The internal rotation type air inlet is a hypersonic air inlet form with unique advantages, has the advantages of short axial distance, small infiltration area, good flow capture characteristic, and the like, is beneficial to the integrated design with the wave-rider precursor, and has been widely concerned by students in all countries in the world in recent years.
The internal rotation type air inlet channel has a complex wave system structure and strong shock wave/boundary layer interference three-dimensional characteristics, so that the flow field structure is complex, and compared with other types of air inlet channel flow fields, the internal rotation type air inlet channel has stronger three-dimensional characteristics, and the strong three-dimensional flow characteristics have larger influence on the flow field parameter distribution and the aerodynamic performance of the air inlet channel. Researches find that low-energy flow accumulation is aggravated by three-dimensional flow direction vortex induced by lip cover shock wave/boundary layer interference, the nonuniformity of flow field parameter distribution is enhanced, and the performance of an air inlet channel is deteriorated. Therefore, in order to further improve the flow of the air inlet and improve the performance of the air inlet, obtaining a complicated flow field structure of the air inlet is a key link. Although basic knowledge and understanding of the structure of the flow field of the counter-rotating inlet channel can be obtained by a numerical simulation method, effective flow field observation technology needs to be developed for verification and supplement.
At present, various test measurement technologies have certain limitations. The schlieren method is commonly used, but only can observe the macroscopic wave structure of the unblocked part of the flow field and is influenced by the along-the-way integral effect. Along-the-way pressure distribution measurement can only obtain data of a limited point in each test due to limited spatial resolution, and the description of the structure of the flow field is limited. The existing laser particle imaging observation technology mainly adopts two-dimensional slice imaging, cannot well acquire a three-dimensional flow field structure, and is also disturbed by light path shielding. In the three-dimensional near-wall flow display, the oil flow display technology has the advantages of simplicity in operation, good economy, capability of intuitively and quickly reflecting the near-wall flow and the like, and is widely applied to flow field display. The oil flow display technology has strict requirements on the preparation and brushing modes of the oil agent and the test recording process. The traditional oil flow display test mostly adopts an even smearing type and a point smearing type to process the surface of a model, has poor adaptability to the distribution of the shearing stress of different positions on the surface of the model, and cannot obtain a clear and vivid oil flow map. Under the high/supersonic flow condition, the incoming flow density is low, the shearing force is relatively small, the difference of the shearing force at different parts of the air inlet channel is relatively large, the adaptability of the wall surface to the traditional uniform brushing mode is poorer, the temperature is relatively high, the oil agent is volatile, and the adverse factors are more prominent in the internally rotating air inlet channel with the wave-rider with strong three-dimensional characteristics. Meanwhile, the influence of the closing of the wind tunnel on the structure change of the oil flow pattern on the near wall surface is avoided as much as possible in the test. Therefore, it is necessary to develop a real-time oil flow display technology suitable for the internal rotation type air inlet with riding front.
Disclosure of Invention
The purpose of the invention is as follows: the invention provides a real-time oil flow display method suitable for a three-dimensional internal rotation type air inlet channel, which solves the problems of adverse effects of flow field changes in the closing process of a wind tunnel and display of a near-wall surface complex flow field structure of the air inlet channel.
The invention also provides an oil agent adopted by the display method.
The technical scheme is as follows: in order to achieve the above object, the present invention provides a real-time oil flow display method with a wave-rider forebody internal rotation type air inlet channel, comprising the following steps:
(1) preparing two oil agents, including a first oil agent and a second oil agent, wherein the first oil agent comprises titanium dioxide, silicone oil and oleic acid, and the mass percentages of the components are as follows: 23-27% of titanium dioxide, 23-27% of silicone oil and 46-54% of oleic acid, wherein the mass percentages of the titanium dioxide and the silicone oil are 1: 1; the second oil agent comprises titanium dioxide, silicone oil and oleic acid, and the mass percentages of the components are as follows: 31-35% of titanium dioxide, 31-35% of silicone oil and 30-38% of oleic acid, wherein the mass percentages of the titanium dioxide and the silicone oil are 1: 1. then, calibrating the first oil agent and the second oil agent, and if a clear oil flow trace is not obtained, continuously adding oleic acid with the total mass of 3-5% of that of the oil agents for debugging until the first oil agent and the second oil agent both meet the experimental requirements;
(2) dipping a first oiling agent by using a brush, uniformly coating the first oiling agent on a first test plate, and blowing air to the test plate close to the wall by using a high-pressure air gun in a direction perpendicular to the brushing direction on the test plate after coating; dipping a second oiling agent by using a brush, uniformly coating the second oiling agent on a second test plate, and blowing air to the second test plate close to the wall by using a high-pressure air gun in a direction perpendicular to the brushing direction on the test plate after coating; the material of the first test plate is the same as that of a wave-rider front compression surface of the three-dimensional inward rotation type air inlet channel test model; the material of the second test plate is the same as that of the air inlet compression surface material of the three-dimensional inward rotation type air inlet test model;
(3) observing oil flow stripes on the surfaces of the first test plate and the second test plate, if the stripe traces are clear, finishing the modulation of the first oil agent and the second oil agent, otherwise, continuously adding oleic acid accounting for 3-5% of the total mass of the first oil agent into the first oil agent, continuously adding oleic acid accounting for 3-5% of the total mass of the second oil agent into the second oil agent, and repeating the step (2) until the oil flow stripes with clear traces on the first test plate and the second test plate are observed;
(4) installing a three-dimensional inward rotation type air inlet test model into a test cabin, wherein the three-dimensional inward rotation type air inlet test model comprises a wave-rider precursor compression surface and an air inlet compression surface, and dipping a first oil agent by a brush to uniformly brush the wave-rider precursor compression surface; dipping a second oil agent by a brush, and uniformly brushing the compressed surface of the air inlet channel; the coating of the second oil agent on the compression surface of the air inlet channel is thicker than the coating of the first oil agent on the compression surface of the waverider precursor;
(5) starting light source systems arranged on observation windows on two outer sides and above an inner side of the test chamber;
(6) and closing the test cabin door, preparing for blowing, and continuously shooting the development and evolution process of the oil flow diagram before the wind tunnel is opened and after the wind tunnel is closed by the camera in real time at the top observation window.
Furthermore, the wind tunnel test section is closed, only an observation window for high-definition shooting is reserved, and external light interference is reduced.
Further, the wind tunnel test section flow field observation area light source system adopts LED light sources which are respectively arranged on two sides and above the three-dimensional inward rotation type air inlet channel test model.
Further, the test chamber is arranged in an air suction type free jet type wind tunnel.
Further, a high-definition camera is adopted to shoot a flow field display area in real time in the test process, and the dynamic change process of the oil flow map is obtained.
Has the advantages that: the invention provides a real-time oil flow display test for an inward-rotation type air inlet of a band-multiplier precursor. The closed test chamber is dark, the shooting brightness can be improved by adding the light source system, and the external light interference is reduced; the following performance of the titanium dioxide tracing particles used for preparing the oil agent is good, and the preparation and calibration method is simple; the shear stress of the compression surface of the waverider precursor is relatively small, and a first oil agent is adopted; the compression surface of the air inlet channel has relatively large shear stress, and a second oiling agent is adopted, and the compression surface coating of the air inlet channel needs to be thicker than the compression surface coating of the wave-multiplying precursor, so that an oil flow map with clear traces is easier to form; the influence of the wind tunnel closing process on an oil flow result can be avoided through real-time recording, a near-wall oil flow map with a stable flow field and a dynamic development process of the oil flow map are obtained, and the method has the characteristics of simplicity, convenience, intuition, rapidness and high display degree.
Drawings
FIG. 1 is a schematic view of a wind tunnel structure for performing a real-time oil flow test according to the present invention.
FIG. 2 is a schematic diagram of the overall test layout of the present invention in performing a real-time oil flow test.
FIG. 3 shows the results of oil application to the test surfaces of the model.
Fig. 4 is a graph of oil flow patterns and comparison of experimental and simulation calculations for the present invention in the performance of an oil flow test.
In the figure, 31 denotes an air inlet, 32 denotes a butterfly valve, 33 denotes a rectifying section, 34 denotes a Laval nozzle, 35 denotes a test chamber, 36 denotes a top observation window, 37 denotes a both-side observation window, 38 denotes a model mounting platform, 39 denotes a diffuser, 40 denotes a gate valve, 41 denotes a vacuum spherical tank, 1 denotes a closed test chamber, 2 denotes a camera, 3 denotes a top observation window, 4 denotes a test model, 5 denotes a light source system, 51 denotes a waverider precursor compression surface brushing result, and 52 denotes an air intake compression surface brushing result.
Detailed Description
Referring to fig. 1 and fig. 2, the related contents related to the real-time oil flow display test of the internal rotation type intake duct with multiplied wave front according to the present invention are shown. The principles, construction and embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
Referring to fig. 1, the test was performed on a Supersonic air Inlet Mechanism test bench (SIMTP) of the university of aerospace. The wind tunnel belongs to an air suction type free jet wind tunnel and comprises an air inlet 31, a butterfly valve 32, a rectifying section 33, a Laval spray pipe 34, a test chamber 35, a top observation window 36, two side observation windows 37, a model mounting platform 38, a diffuser 39, a gate valve 40 and a vacuum spherical tank 41, wherein the two sides and the top of the test section are provided with optical observation windows. The total incoming flow parameter is a local atmospheric environment parameter. The nominal Mach number of the incoming flow in the test is Ma3.0, the effective test time is 15-20s, and the detailed test parameters are shown in Table 1.
TABLE 1 test parameter ranges provided by wind tunnels
The oil used in the real-time oil flow test implemented by the invention adopts titanium dioxide particles as tracer particles, silicon oil as carrier oil and oleic acid as an additive. According to different mass percentages of oleic acid in the oil, two different oil agents are prepared, one is that a large amount of oleic acid is added, and particles precipitate after standing for a long time; the other is that a small amount of oleic acid is added, and no particles precipitate after standing for a long time. The titanium dioxide tracer particles should be sufficiently dried and no agglomeration can occur. The tools for preparing and brushing the oil agent comprise a measuring cup, a dropper, a stirring rod, a stirrer and a brush. The test steps mainly comprise: the method comprises the following steps of model installation, surface cleaning, oil agent preparation, oil agent brushing, test chamber sealing, light source opening, blowing test and shooting, wherein the oil agent preparation, the oil agent brushing, the test chamber sealing, the light source opening and the shooting are key steps of the method. The frame rate of the camera used during the wall oil flow test was about 15 frames/s.
The preparation, brushing and calibration methods and test processes of the oil agent are as follows: (1) taking a proper amount of titanium dioxide by using a measuring cylinder, pouring the titanium dioxide into a beaker, simultaneously adding silicon oil with the viscosity of 50cs into the beaker, and stirring until the mixed oil agent is free from agglomeration, wherein the mass percentages of the titanium dioxide and the silicon oil are as follows: 50% of titanium dioxide and 50% of silicone oil. The operation should be carried out twice, namely two cups of oil agent without oleic acid are prepared, and the label area is pasted to be divided into a first oil agent and a second oil agent. (2) Adding a large amount of oleic acid into the first oil agent, and uniformly stirring, wherein the mass percentages of titanium dioxide, silicone oil and oleic acid are as follows: 23-27% of titanium dioxide, 23-27% of silicone oil and 46-54% of oleic acid, wherein the mass percentage of the titanium dioxide and the silicone oil is 1: 1, the addition amount of oleic acid can be properly adjusted on the basis: when the titanium dioxide and the silicone oil account for 23 percent by mass and the oleic acid accounts for 54 percent by mass, the prepared first oil agent has the strongest flowability in the range of the mixture ratio of the components; when the titanium dioxide and the silicone oil account for 27 percent by mass and the oleic acid accounts for 46 percent by mass, the prepared first oil agent has the weakest mobility in the range of the proportion of each component; when the mass percentages of the first oil agent, the second oil agent and the third oil agent are in the middle value of the given range, the fluidity of the first oil agent is between the strongest and the weakest, and the mass ratio scheme of the components of the first oil agent finally selected in the experiment is also provided. Through repeated experimental exploration, the first oil agent meeting the conditions can be effectively prepared within the given mass percentage range of each component, and the first oil agent is selected according to the actual treatment condition of the surface of an experimental model. (3) Adding a small amount of oleic acid into the second oil agent, and uniformly stirring, wherein the mass percentages of titanium dioxide, silicone oil and oleic acid are 31-35% of titanium dioxide, 31-35% of silicone oil and 30-38% of oleic acid, wherein the mass percentages of titanium dioxide and silicone oil are 1: 1, the addition amount of oleic acid can be properly adjusted on the basis: when the titanium dioxide and the silicone oil account for 31 percent by mass and the oleic acid accounts for 38 percent by mass, the prepared second oil agent has the strongest flowability in the range of the mixture ratio of the components; when the titanium dioxide and the silicone oil account for 35 percent by mass and the oleic acid accounts for 30 percent by mass, the prepared second oil agent has the weakest mobility in the proportion range of each component; when the mass percentages of the first oil agent, the second oil agent and the third oil agent are in the middle of the given ranges, the flowability of the second oil agent is between the strongest and the weakest, and the mass ratio scheme of the components of the second oil agent finally selected in the experiment is also provided. Through repeated experimental exploration, the second oil agent meeting the conditions can be effectively prepared within the given mass percentage range of each component, and the second oil agent is selected according to the actual treatment condition of the surface of an experimental model. (4) Dipping a first oiling agent by using a brush, uniformly coating the first oiling agent on a first test plate, and blowing air to the test plate close to the wall by using a high-pressure air gun in a direction perpendicular to the brushing direction on the test plate after coating; and dipping the second oiling agent by using a brush to uniformly smear on the second test plate, and blowing air to the wall of the second test plate by using a high-pressure air gun in a direction perpendicular to the brushing direction on the test plate after smearing. The material of the first test plate is the same as that of a wave-rider front compression surface of the three-dimensional inward rotation type air inlet channel test model; the material of the second test plate is the same as that of the air inlet compression surface material of the three-dimensional inward rotation type air inlet test model. In the present embodiment, the first and second test plates are of an integral structure. (5) And (4) observing oil flow stripes on the surface of the flat plate, if the stripes are clear, finishing the preparation of the oil agent, otherwise, continuously adding oleic acid accounting for 3-5% of the total mass of the oil agent, and repeating the step (4) until the oil flow stripes with clear traces are observed. 3% -5% of oleic acid can effectively control the prepared oil agent in the range required by the experiment: if the addition amount is too much, the oil agent is easy to be excessively diluted, the fluidity is too strong, and the preparation of the oil agent needs to be restarted; if the addition amount is too small, the addition amount needs to be repeatedly added for many times, and unnecessary complexity is increased for the oil preparation process. (6) And installing the test model into the test cabin. (7) The surface of the model was cleaned with alcohol soaked sanitary napkin until there was no dust particles on the surface of the model. (8) Dipping a first oil agent by a brush to brush the compressed surface of the wave-multiplying precursor, wherein the coating needs to be uniform and slightly leaks the natural color of the model; and (3) dipping a second oil agent by a brush to brush the compressed surface of the air inlet, wherein the coating is uniform and basically does not leak out of the natural color of the model, and the compressed surface coating of the air inlet is thicker than the compressed surface coating of the wave-multiplying precursor. As shown in fig. 3, the part designated by reference numeral 51 is the result of brushing the first oil agent on the compression surface (first test plate) of the waverider precursor; the portion designated 52 is the result of the second oil application on the compression side of the inlet (second test panel). (9) And the light source systems arranged on the observation windows at the two outer sides and the upper part of the inner side of the test chamber are started, and the light source systems arranged at the two sides of the test chamber play a role in closing the test chamber. (10) And closing the test cabin door, preparing for blowing, and continuously shooting the development and evolution process of the oil flow diagram before the wind tunnel is opened and after the wind tunnel is closed by the camera in real time at the top observation window. Fig. 4 shows an oil flow diagram of the oil flow test and a comparison between the test and the simulation calculation. It can be seen from the figure that in the real-time oil flow display test, clear and stable oil flow maps of the compression surface of the wave-rider precursor and the compression surface of the air inlet channel can be obtained at the same time, so that the problem that the compression surface of the wave-rider precursor is not blown or the oil agent on the compression surface of the air inlet channel is blown excessively due to the fact that oil agent is not coated in a traditional oil flow test is solved, and the adverse effect of flow field change in the closing process of the wind tunnel is avoided. (11) And judging and analyzing test data, removing residual oil on the surface of the model, and preparing the next blowing test.
Oil formulation is the first key point of the present invention. The titanium dioxide particles are fine and have good followability, and the preparation and calibration methods are simple and quick.
The second key point of the invention is that the wave-rider precursor compression surface and the air inlet compression surface are coated in a distributed mode according to the magnitude of the surface shearing force of the model. The compression surface of the wave-rider precursor is subjected to small shear stress, and the compression surface of the air inlet channel is subjected to relatively large shear stress. The selection of the oil solution and the relative thickness of the two coatings are properly adjusted according to different positions of the model, so that the clear and complete oil flow map of the stripe trace can be obtained.
A closed test chamber is the third key point of the present invention. The purpose is to reduce external light interference. As shown in the figure 2, a camera 2 and a top observation window 3 are arranged on the closed test chamber 1, and the camera 2 shoots the internal image of the test chamber from the top observation window 3. The test model 4 is mounted in the closed test chamber 1 and a light source system 5 is provided for illumination. Configuring the light source system 5 is a fourth key point of the present invention. The problem of serious insufficient brightness exists in a closed test section observation area, and the light source system can increase the shooting brightness.
Real-time recording is the fifth key point of the present invention. The method can conveniently judge whether the flow reaches a stable state, has the characteristics of intuition and rapidness, and has the key that the oil flow stripes can not be influenced by the change of the closed flow field of the air holes.
The invention embodies a number of methods and approaches to this solution and the foregoing is only a preferred embodiment of the invention. It should be noted that, for those skilled in the art, without departing from the principle of the present invention, several improvements and modifications can be made, and these improvements and modifications should also be construed as the protection scope of the present invention. All the components not specified in the present embodiment can be realized by the prior art.
Claims (5)
1. A real-time oil flow display method for an internal rotation type air inlet channel with a wave-rider front body is characterized by comprising the following steps of:
(1) preparing two oil agents, including a first oil agent and a second oil agent, wherein the first oil agent comprises titanium dioxide, silicone oil and oleic acid, and the mass percentages of the components are as follows: 23-27% of titanium dioxide, 23-27% of silicone oil and 46-54% of oleic acid, wherein the mass percentages of the titanium dioxide and the silicone oil are 1: 1; the second oil agent comprises titanium dioxide, silicone oil and oleic acid, and the mass percentages of the components are as follows: 31-35% of titanium dioxide, 31-35% of silicone oil and 30-38% of oleic acid, wherein the mass percentages of the titanium dioxide and the silicone oil are 1: 1;
(2) dipping a first oiling agent by using a brush, uniformly coating the first oiling agent on a first test plate, and blowing air to the test plate close to the wall by using a high-pressure air gun in a direction perpendicular to the brushing direction on the test plate after coating; dipping a second oiling agent by using a brush, uniformly coating the second oiling agent on a second test plate, and blowing air to the second test plate close to the wall by using a high-pressure air gun in a direction perpendicular to the brushing direction on the test plate after coating; the material of the first test plate is the same as that of a wave-rider front compression surface of the three-dimensional inward rotation type air inlet channel test model; the material of the second test plate is the same as that of the air inlet compression surface material of the three-dimensional inward rotation type air inlet test model;
(3) observing oil flow stripes on the surfaces of the first test plate and the second test plate, if the stripe traces are clear, finishing the modulation of the first oil agent and the second oil agent, otherwise, continuously adding oleic acid accounting for 3-5% of the total mass of the first oil agent into the first oil agent, continuously adding oleic acid accounting for 3-5% of the total mass of the second oil agent into the second oil agent, and repeating the step (2) until the oil flow stripes with clear traces on the first test plate and the second test plate are observed;
(4) installing a three-dimensional inward rotation type air inlet test model into a test cabin, wherein the three-dimensional inward rotation type air inlet test model comprises a wave-rider precursor compression surface and an air inlet compression surface, and dipping a first oil agent by a brush to uniformly brush the wave-rider precursor compression surface; dipping a second oil agent by a brush, and uniformly brushing the compressed surface of the air inlet channel; the coating of the second oil agent on the compression surface of the air inlet channel is thicker than the coating of the first oil agent on the compression surface of the waverider precursor;
(5) starting light source systems arranged on observation windows on two outer sides and above an inner side of the test chamber;
(6) and closing the test cabin door, preparing for blowing, and continuously shooting the development and evolution process of the oil flow diagram before the wind tunnel is opened and after the wind tunnel is closed by the camera in real time at the top observation window.
2. The display method according to claim 1, wherein: the wind tunnel test section is closed, only an observation window for high-definition shooting is reserved, and external light interference is reduced.
3. The display method according to claim 1, wherein: the wind tunnel test section flow field observation area light source system adopts an LED light source and is respectively arranged on two sides and above the side of a three-dimensional inward rotation type air inlet channel test model.
4. The display method according to claim 1, wherein: the test chamber is installed in an air-breathing free jet type wind tunnel.
5. The display method according to claim 1, wherein: and in the test process, a high-definition camera is adopted to shoot a flow field display area in real time, so that the dynamic change process of the oil flow map is obtained.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010546271.2A CN111811769B (en) | 2020-06-16 | 2020-06-16 | Three-dimensional internal rotation type air inlet channel real-time oil flow display method with wave-rider precursor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010546271.2A CN111811769B (en) | 2020-06-16 | 2020-06-16 | Three-dimensional internal rotation type air inlet channel real-time oil flow display method with wave-rider precursor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN111811769A CN111811769A (en) | 2020-10-23 |
| CN111811769B true CN111811769B (en) | 2021-08-06 |
Family
ID=72845134
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202010546271.2A Active CN111811769B (en) | 2020-06-16 | 2020-06-16 | Three-dimensional internal rotation type air inlet channel real-time oil flow display method with wave-rider precursor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN111811769B (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112985822B (en) * | 2021-04-20 | 2021-08-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Air inlet channel test device for simulating coupling effect of air inlet channel and fan |
| CN114166463B (en) * | 2022-02-14 | 2022-05-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Oil flow map and surface pressure fusion simulation visualization method |
| CN115371950B (en) * | 2022-10-21 | 2023-01-17 | 中国航空工业集团公司沈阳空气动力研究所 | Fluorescent color oil flow spectrum three-dimensional reconstruction formula and method suitable for inner pipeline |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102533109A (en) * | 2011-12-14 | 2012-07-04 | 中国航空工业集团公司沈阳空气动力研究所 | Oil formula of high speed wind tunnel colorful oil flow experiment |
| CN203581388U (en) * | 2013-12-11 | 2014-05-07 | 厦门大学 | High-supersonic aircraft and air inlet channel internal and external waverider integration device |
| CN108489703A (en) * | 2018-03-23 | 2018-09-04 | 西北工业大学 | A kind of colorful oil flow formula suitable for high-speed wind tunnel for clearly demarcating range of Mach numbers |
| CN108760225A (en) * | 2018-04-03 | 2018-11-06 | 西北工业大学 | A kind of oil stream formula of the high-speed wind tunnel oil stream experiment of clearly calibration range of Mach numbers |
| CN108896270A (en) * | 2018-04-03 | 2018-11-27 | 西北工业大学 | A kind of oil stream formula of low-speed wind tunnel oil stream experiment that clearly demarcating range of Mach numbers |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10230757A1 (en) * | 2002-07-09 | 2004-01-22 | Zf Friedrichshafen Ag | Method and device for machine diagnosis and in particular for transmission diagnosis |
| CN110057535A (en) * | 2019-05-27 | 2019-07-26 | 中国空气动力研究与发展中心 | Shock tunnel judges the wall surface silk thread Method of flow visualization and system of intake duct starting |
| CN112014064B (en) * | 2020-10-27 | 2021-01-05 | 中国空气动力研究与发展中心高速空气动力研究所 | Wind tunnel complex flow color fluorescent oil flow test method |
-
2020
- 2020-06-16 CN CN202010546271.2A patent/CN111811769B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102533109A (en) * | 2011-12-14 | 2012-07-04 | 中国航空工业集团公司沈阳空气动力研究所 | Oil formula of high speed wind tunnel colorful oil flow experiment |
| CN203581388U (en) * | 2013-12-11 | 2014-05-07 | 厦门大学 | High-supersonic aircraft and air inlet channel internal and external waverider integration device |
| CN108489703A (en) * | 2018-03-23 | 2018-09-04 | 西北工业大学 | A kind of colorful oil flow formula suitable for high-speed wind tunnel for clearly demarcating range of Mach numbers |
| CN108760225A (en) * | 2018-04-03 | 2018-11-06 | 西北工业大学 | A kind of oil stream formula of the high-speed wind tunnel oil stream experiment of clearly calibration range of Mach numbers |
| CN108896270A (en) * | 2018-04-03 | 2018-11-27 | 西北工业大学 | A kind of oil stream formula of low-speed wind tunnel oil stream experiment that clearly demarcating range of Mach numbers |
Non-Patent Citations (2)
| Title |
|---|
| Fractal features of turbulent/nonturbulent interface in a shock wave/turbulent boundary layer interaction flow;Zhuang Yi;《Journal of fluid mechanics》;20190625;全文 * |
| 脉冲燃烧风洞点式油流技术在压缩拐角流动显示中的应用;王振锋;《推进技术》;20141130;第1455-1460页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN111811769A (en) | 2020-10-23 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN111811769B (en) | Three-dimensional internal rotation type air inlet channel real-time oil flow display method with wave-rider precursor | |
| CA3055138C (en) | Surface reactivation treatment | |
| CN105840382B (en) | A kind of evaluation method and measuring device of each spray orifice uniformity of fuel injector | |
| CN106908214A (en) | The collocation method and experiment finish of high-speed wind tunnel oil stream experiment finish | |
| CN106840576A (en) | High-speed wind tunnel oil stream test method | |
| CN111737822A (en) | Point cloud data-based three-dimensional morphology evaluation method for fitting clearance of aviation component | |
| CN106441807A (en) | Experimental system and experimental method for fog experiment of automobile headlamp | |
| RU2334206C1 (en) | Two-stage jet engine simulator | |
| CN106197941B (en) | A kind of icing mnncl tcst wing model for aircraft certification verifying | |
| CN108303520B (en) | A kind of defeated paint mixing system shrinkage cavity test method of painting dressing automobiles | |
| CN112014064B (en) | Wind tunnel complex flow color fluorescent oil flow test method | |
| CN103743537B (en) | For pressurize delivery device and the method for PIV experiment trace particle | |
| CN108760225A (en) | A kind of oil stream formula of the high-speed wind tunnel oil stream experiment of clearly calibration range of Mach numbers | |
| CN110987356A (en) | Formula and using method of colored oil flow suitable for subsonic velocity temporary flushing wind tunnel | |
| Bridges et al. | PIV measurements of a low-noise top-mounted propulsion installation for a supersonic airliner | |
| CN203758718U (en) | Pressure maintaining put-in device used for PIV experiment tracer particle | |
| CN110646161B (en) | Measured object surface treatment method for oil film interference measurement | |
| RU67258U1 (en) | INSTALLATION FOR AERODYNAMIC TESTS OF THE MODEL OF THE AIR INTAKE OF THE ENGINE OF THE AIRCRAFT ENGINE (OPTIONS) | |
| CN115371950B (en) | Fluorescent color oil flow spectrum three-dimensional reconstruction formula and method suitable for inner pipeline | |
| CN116068327B (en) | Aging control cabinet testing device based on electrical property detection | |
| CN214952929U (en) | Pollution test box | |
| CN112304559B (en) | Natural gas flow field test system | |
| CN216847391U (en) | Salt spray testing machine | |
| CN116878540A (en) | Observation experiment method and system for influence of high-speed mixed flow field on deflection of navigation starlight | |
| Kille et al. | Side Mirror Soiling Investigation through the Characterization of Water Droplet Formation and Size behind a Generic Plate |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |