CN108918078A - A kind of hypersonic oil film interferometry frictional resistance measurement experiment device and experimental method - Google Patents
A kind of hypersonic oil film interferometry frictional resistance measurement experiment device and experimental method Download PDFInfo
- Publication number
- CN108918078A CN108918078A CN201810453837.XA CN201810453837A CN108918078A CN 108918078 A CN108918078 A CN 108918078A CN 201810453837 A CN201810453837 A CN 201810453837A CN 108918078 A CN108918078 A CN 108918078A
- Authority
- CN
- China
- Prior art keywords
- hypersonic
- oil film
- frictional resistance
- pressure
- experimental
- 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.)
- Pending
Links
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
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
- G01N21/00—Investigating or analysing materials by the use of optical means, i.e. using sub-millimetre waves, infrared, visible or ultraviolet light
- G01N21/17—Systems in which incident light is modified in accordance with the properties of the material investigated
- G01N21/41—Refractivity; Phase-affecting properties, e.g. optical path length
- G01N21/45—Refractivity; Phase-affecting properties, e.g. optical path length using interferometric methods; using Schlieren methods
Landscapes
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Life Sciences & Earth Sciences (AREA)
- Chemical & Material Sciences (AREA)
- Analytical Chemistry (AREA)
- Biochemistry (AREA)
- General Health & Medical Sciences (AREA)
- Immunology (AREA)
- Pathology (AREA)
- Fluid Mechanics (AREA)
- Compositions Of Macromolecular Compounds (AREA)
Abstract
The present invention relates to a kind of hypersonic oil film interferometry frictional resistance measurement experiment devices and experimental method, the device to include：Hypersonic wind tunnel, high-pressure air source, high-pressure sodium lamp, high speed camera, experimental model, analysis level silicone oil, thermocouple.By plating black titanium to experimental model surface, the condition of surface smoothness, refractive index and high temperature is met；In experiment, reasonable incoming flow stagnation pressure and silicon oil viscosity are selected, reduces blow-time；Again by thermocouple temperature measurement, temperature calibration is carried out to silicon oil viscosity；Finally skin friction resistance coefficient is calculated from the formula using the experimental data measured.The device and method have precision high, and time of measuring is fast, feature at low cost.
Description
Technical field
The present invention is to be related to a kind of wind tunnel test coefficient of frictional resistance measuring device and method, and in particular to a kind of high ultrasound
The experimental provision and method of oil film interferometry measurement coefficient of frictional resistance are utilized under the conditions of speed.
Technical background
Aircraft surface frictional resistance occupies a big chunk of drag overall in flight course, for passenger plane and large-scale fortune
For defeated machine, the size of skin friction resistance has a great impact for voyage and payload, for hypersonic aircraft
For, the size of skin friction resistance then affects the thermal protection system of surface heat flow and aircraft.Therefore, for aircraft table
The measurement of face frictional resistance just seems particularly significant.
Oil film interferometry is a kind of simple, effective coefficient of frictional resistance measurement method.Oil film interferometry measures table at present
Face coefficient of frictional resistance has had sufficient application, the good effect of acquirement in low speed, subsonic speed and Supersonic Stream.
But hypersonic inlet flow conditions and above-mentioned condition are very different, for example, hypersonic incoming flow total temperature is very high, cause to test
Segment model wall surface temperature is higher, and common Mylar film cannot be pasted onto model surface well in low speed experiment.Therefore for height
Supersonic Stream condition, oil film interferometry coefficient of friction resistance measuring technique need biggish improvement.
Existing literature is (for achievement, Zhang Changfeng, yellow hurricane, the hypersonic skin friction stress oil film interferometry skill of Zhou Qingzhan
Art research [J] experimental fluid mechanics, 2012,26 (02):It 68-71+85.) announces under a kind of hypersonic inlet flow conditions, utilizes
The experimental method of oil film interferometry measurement skin friction stress.Wind-tunnel incoming flow stagnation pressure is big in document experiment, has selected viscosity larger
Silicone oil, blow-time is longer, at high cost；And since long-time is dried, when oil film fringe spacing is by incoming flow disturbance
Between it is long, affect the reading of fringe spacing, cause experimental error；Silicon oil viscosity is greatly influenced by temperature, and blowing is made for a long time
At the variation of test model wall surface temperature, the size of silicon oil viscosity is affected, experimental error is also resulted in.
Therefore, under the conditions of hypersonic, existing oil film interference experiment method there is also very big deficiency, need into
Row improves, and can either improve experimental precision, and can be reduced experimental cost.
Summary of the invention
Technical problem solved by the invention is to provide a kind of hypersonic oil film interference friction resistance coefficient measuring device
And method, model surface coefficient of frictional resistance can be obtained using oil film interferometry under hypersonic inlet flow conditions, improved real
Precision is tested, experimental cost is reduced.
The present invention provides a kind of hypersonic oil film interference frictional resistance measurement experiment device：Including hypersonic wind tunnel, high pressure
Gas source, high-pressure sodium lamp, high speed camera, experimental model, analysis level silicone oil, thermocouple.
As a preferred solution of the present invention, the hypersonic wind tunnel tests Mach number Ma=5.Ma=5 is superb
Velocity of sound typical case's Mach number.
As a preferred solution of the present invention, 5 atmospheric pressure are set as in the high-pressure air source experiment, i.e. experiment stagnation pressure
For 5 atmospheric pressure.
As a preferred solution of the present invention, the high-pressure sodium lamp power 400W issues the monochromatic light of wavelength 589nm.
The sodium vapor lamp be placed on the hypersonic wind tunnel stay interior, for illuminating the surface of the experimental model.
As a preferred solution of the present invention, the high speed camera is the CCD high speed camera of HotShot company, collocation
Nikon50-200mm zoom lens, camera filming frequency are 100Hz.The high speed camera is placed on the sight in the portion in ceiling
It examines on window.
As a preferred solution of the present invention, the experimental model uses flat plate model.
As a preferred solution of the present invention, the experimental model surface plates one layer of black titanium, and it is good to guarantee that surface has
Good finish and refractive index, and being capable of high temperature resistant.
As a preferred solution of the present invention, it is the aperture of 1mm that, which there is diameter in experimental model model test region,.
As a preferred solution of the present invention, the thermocouple is placed in the aperture.
As a preferred solution of the present invention, the thermocouple probe and the flat plate model flush.
As a preferred solution of the present invention, viscosity is 50mPas under the analysis level silicone oil normal temperature state.
As a preferred solution of the present invention, the analysis level silicone oil is applied to the experiment at the thermocouple location
The surface of model.
For the experimental method of above-mentioned hypersonic oil film interference friction measurement experiment device, realized by following step：
Step 1：The experimental model test zone is illuminated using the sodium vapor lamp.
Step 2：The high speed camera angle is adjusted, so that test zone is high-visible, and carries out calibrating length.
Step 3：The analysis level silicone oil is painted along straight line in the model surface test zone.Oily line just covers institute
State position of thermocouple.
Step 4：It is 5 atmospheric pressure that the high-pressure air source, which is arranged, is blown in, and blow-time is 7~8 seconds.
Step 5：Using the stripe order recognition image of the analysis level silicone oil during high speed camera shooting blowing, simultaneously
Utilize test zone temperature variations during thermocouple record blowing.
Step 6：It is respectively t that access time, which is separated by shooting time,1And t2Two oil-film images, utilize image processing software
And theoretical analysis method carries out data processing：
1. according to oil film interference friction resistance coefficient calculation formula：
N in formula Chinese style0Indicate the refractive index of silicone oil, θ indicates refraction angle, and N represents the fringe order of calculating, and λ indicates examination
Test the wavelength of the monochromatic sodium vapor lamp of middle selection, t1And t2Respectively represent the initial time of oil film pattern shooting and by moment, above-mentioned ginseng
Number is known in an experiment.
2. Δ x indicates the total distance that N grades of stripeds move between two moment：
Δ x=Δ x (t2)-Δx(t1)
Wherein Δ x (t1) and Δ x (t2) respectively represent t1And t2The N grade oil film fringe spacing at moment.
3.q∞(t) the incoming flow dynamic pressure of different moments is indicated.In the case where hypersonic Ma=5, fluid has very strong
Compressibility, therefore the calculating formula of incoming flow dynamic pressure：
Middle density p∞With speed of incoming flow V∞It is all unknown quantity, incoming flow dynamic pressure q∞It can not be calculated.So dynamic pressure q∞Meter
Calculate the Bernoulli equation for using compressible flow：
In conjunction with one dimensional isentropic flow basic relational expression：
Derive dynamic pressure q∞Calculating formula：
γ represents the specific heat ratio of air in formula, is constant 1.4 in experiment；Ma represents experiment Mach number, Ma=5；p0And ρ0
Stagnation pressure and gross density are respectively represented, p and ρ represent static pressure and quiet density.Wherein p0It is set as 5 atmospheric pressure.
4. μ (t) indicates to test the viscosity of silicone oil different moments used.It is quasi- according to the Temperature-Viscosity of the analysis level silicone oil
Curve is closed, in conjunction with the temperature that the thermocouple measures, obtains t1And t2Film viscosity μ (the t at moment1) and μ (t2)。
5. the parameter of above-mentioned acquisition is brought into coefficient of frictional resistance calculation formula, rubbing for model surface measurement point is acquired
Wipe resistance coefficient.
Hypersonic oil film interference frictional resistance measurement experiment device of the present invention and its experimental method have the following advantages that：
1. present invention improves over low speed oil film interference experiment model surface processing method, by model surface black coating titanium,
Instead of the method for traditional stickup Mylar film, it both ensure that the refractive index of the finish of model surface, and also compensated for Mylar
The shortcomings that film can not be pasted under high temperature environment.
2. the present invention realizes under the conditions of identical Mach number, reasonable hypersonic incoming flow stagnation pressure and appropriate viscosity are set
Silicone oil, achieve good experimental result, and reduce experimental period, cost be greatly saved.
3. the present invention is acted upon by temperature changes to silicon oil viscosity and is demarcated such as Fig. 5, the precision of experiment is improved.
Detailed description of the invention
The present invention will be further described with reference to the accompanying drawings and examples.
Fig. 1 is experimental provision arrangement schematic diagram of the present invention
Fig. 2 is experimental model test zone detail view of the present invention
Fig. 3 is experimental method flow chart of steps of the present invention
Fig. 4 is different moments t of the invention1、t2Oil film striped schematic diagram
Fig. 5 is silicon oil viscosity-temperature influence curve that viscosity is 50mPas under the conditions of 25 DEG C
Fig. 6 is the oil film bar graph (shooting interval 1s) of actual experiment shooting of the present invention
Fig. 7 is influence of the silicone oil temperature adjustmemt to coefficient of frictional resistance measurement experiment result
In attached drawing
10 hypersonic wind tunnels 11 stay 12 observation window of room
20 high-pressure air source, 30 high-pressure sodium lamp, 40 high speed camera
50 experimental model, 60 analysis level silicone oil, 70 thermocouple
Specific embodiment
In order to make the objectives, technical solutions, and advantages of the present invention clearer, with reference to embodiments and attached drawing, right
The present invention is further elaborated.It should be appreciated that the specific embodiments described herein are only used to explain the present invention,
It is not intended to limit the present invention.
Such as Fig. 1, a kind of hypersonic oil film interference frictional resistance measurement experiment device：Including hypersonic wind tunnel (10), high pressure
Gas source (20), high-pressure sodium lamp (30), high speed camera (40), experimental model (50), thermocouple (60), analysis level silicone oil (70).
Such as Fig. 1, hypersonic wind tunnel (10) tests Mach number Ma=5.Ma=5 is hypersonic typical Mach number.
Such as Fig. 1,5 atmospheric pressure are set as in high-pressure air source (20) experiment, i.e., experiment stagnation pressure is 5 atmospheric pressure.
Such as Fig. 1, high-pressure sodium lamp (30) power 400W, the monochromatic light of wavelength 589nm is issued.Sodium vapor lamp is placed on the high ultrasound
Fast wind-tunnel is stayed in room (11), for illuminating the surface of the experimental model.
Such as Fig. 1, high speed camera is the CCD high speed camera of HotShot company, Nikon50-200mm zoom lens of arranging in pairs or groups,
Camera filming frequency is 100Hz.The high speed camera is placed on the observation window (12) in the portion in ceiling.
Such as Fig. 1, experimental model (50) uses flat plate model.
Such as Fig. 1, experimental model (50) surface plates one layer of black titanium, guarantees that surface has good finish and refractive index,
And it being capable of high temperature resistant.
Such as Fig. 2, it is the aperture of 1mm that experimental model (50) measured zone, which has diameter,.
Such as Fig. 2, thermocouple (70) is placed in aperture.
Such as Fig. 2, thermocouple (70) probe and experimental model (50) flush.
Such as Fig. 2, dynamic viscosity coefficient is 50mPas under 25 DEG C of states of analysis level silicone oil (60) room temperature.
Such as Fig. 2, analysis level silicone oil (60) is applied to the surface of the experimental model (50) of thermocouple (70) installed position.Such as
Fig. 3 is realized for the experimental method of above-mentioned hypersonic oil film interference friction measurement experiment device by following step：
Step 1：The experimental model test zone is illuminated using the sodium vapor lamp.
Step 2：The high speed camera angle is adjusted, so that test zone is high-visible, and carries out calibrating length.
Step 3：The analysis level silicone oil is painted along straight line in the model surface test zone.Oily line just covers institute
State position of thermocouple.
Step 4：It is 5 atmospheric pressure that the high-pressure air source, which is arranged, is blown in, and blow-time is 7~8 seconds.
Step 5：Such as Fig. 4, the stripe order recognition figure of the analysis level silicone oil during high speed camera shooting blowing is utilized
Picture, while utilizing test zone temperature variations during thermocouple record blowing.
Step 6：Such as Fig. 4, it is respectively t that access time, which is separated by shooting time,1And t2Two oil-film images, at image
It manages software and theoretical analysis method carries out data processing：
1. according to oil film interference friction resistance coefficient calculation formula：
N in formula Chinese style0Indicate the refractive index of silicone oil, θ indicates refraction angle, and N represents the fringe order of calculating, and λ indicates examination
Test the wavelength of the monochromatic sodium vapor lamp of middle selection, t1And t2Respectively represent the initial time of oil film pattern shooting and by moment, above-mentioned ginseng
Number is known in an experiment.
2. Δ x indicates the total distance that N grades of stripeds move between two moment：
Δ x=Δ x (t2)-Δx(t1)
Wherein Δ x (t1) and Δ x (t2) respectively represent t1And t2The N grade oil film fringe spacing at moment.
3.q∞(t) the incoming flow dynamic pressure of different moments is indicated.In the case where hypersonic Ma=5, fluid has very strong
Compressibility, therefore the calculating formula of incoming flow dynamic pressure：
Middle density p∞With speed of incoming flow V∞It is all unknown quantity, incoming flow dynamic pressure q∞It can not be calculated.So dynamic pressure q∞Meter
Calculate the Bernoulli equation for using compressible flow：
In conjunction with one dimensional isentropic flow basic relational expression：
Derive dynamic pressure q∞Calculating formula：
γ represents the specific heat ratio of air in formula, is constant 1.4 in experiment；Ma represents experiment Mach number, Ma=5；p0And ρ0
Stagnation pressure and gross density are respectively represented, p and ρ represent static pressure and quiet density.Wherein p0It is set as 5 atmospheric pressure.
4. μ (t) indicates to test the viscosity of silicone oil different moments used.Such as Fig. 5, according to the temperature-of the analysis level silicone oil
Viscosity matched curve obtains t in conjunction with the temperature that the thermocouple measures1And t2Film viscosity μ (the t at moment1) and μ (t2)。
5. the parameter of above-mentioned acquisition is brought into coefficient of frictional resistance calculation formula, rubbing for model surface measurement point is acquired
Wipe resistance coefficient.
Hypersonic oil film interference frictional resistance measurement experiment device of the present invention and its experimental method have the following advantages that：
1. present invention improves over low speed oil film interference experiment model surface processing method, by model surface black coating titanium,
Instead of the method for traditional stickup Mylar film, it both ensure that the refractive index of the finish of model surface, and also compensated for Mylar
The shortcomings that film can not be pasted under high temperature environment.
2., for the candy strip obtained in experiment, fringe order is enough, clear-cut texture such as Fig. 6.The present invention realizes
Under the conditions of identical Mach number, the silicone oil of reasonable hypersonic incoming flow stagnation pressure and appropriate viscosity is set, good experiment is achieved
As a result, improving precision, and reduce blow-time, cost is greatly saved.
3. the present invention is acted upon by temperature changes to silicon oil viscosity and is demarcated such as Fig. 5, the precision of experiment is improved.
There are many particular use of the present invention, the above is only a preferred embodiment of the present invention, it is noted that for this skill
For the those of ordinary skill in art field, without departing from the principle of the present invention, several improvement can also be made, these change
Into also should be regarded as protection scope of the present invention.
Claims (9)
1. a kind of hypersonic oil film interferometry frictional resistance measurement experiment device, it is characterised in that：Including hypersonic wind tunnel, high pressure
Gas source, high-pressure sodium lamp, high speed camera, experimental model, analysis level silicone oil, thermocouple.
2. a kind of hypersonic oil film interferometry frictional resistance measurement experiment device as described in claim 1, it is characterised in that：It is described
Hypersonic wind tunnel includes to stay room, observation window, tests Mach number Ma=5.
5 atmospheric pressure are set as in the high-pressure air source experiment, i.e., experiment incoming flow stagnation pressure is 5 atmospheric pressure.
The high-pressure sodium lamp power 400W, issues the monochromatic light of wavelength 589nm, and the sodium vapor lamp is placed on the hypersonic wind tunnel
Stay interior, for illuminating the surface of the experimental model.
The high speed camera is the CCD high speed camera of HotShot company, Nikon50-200mm zoom lens of arranging in pairs or groups, camera shooting
Frequency is 100Hz, and the high speed camera is placed on the observation window in the portion in ceiling of the hypersonic wind tunnel.
The experimental model uses flat plate model.
The experimental model surface plates one layer of black titanium, guarantees that surface has good finish and refractive index, and can be resistant to
High temperature.
It is the aperture of 1mm that the experimental model test area, which has diameter,.
As a preferred solution of the present invention, the thermocouple is placed in the aperture.
The thermocouple probe and the flat plate model flush.
Dynamic viscosity coefficient is 50mPas under the analysis level silicone oil normal temperature state.
3. a kind of hypersonic oil film interferometry frictional resistance measurement experiment device as described in claim 1 and 2, it is characterised in that：
The analysis level silicone oil is applied to the experimental model surface at the thermocouple location.
4. a kind of experiment side of hypersonic oil film interferometry frictional resistance measurement experiment device as described in one of claim 1-3
Method, it is characterised in that：It is realized by following step：
Step 1：The experimental model test zone is illuminated using the sodium vapor lamp；
Step 2：The high speed camera angle is adjusted, so that test zone is high-visible, and carries out calibrating length；
Step 3：The analysis level silicone oil is painted along straight line in the model surface test zone, oily line just covers the heat
Galvanic couple installation site；
Step 4：It is 5 atmospheric pressure that the high-pressure air source, which is arranged, is blown in, and blow-time is 7~8 seconds；
Step 5：Using the stripe order recognition image of the analysis level silicone oil during high speed camera shooting blowing, utilize simultaneously
Test zone temperature variations during the thermocouple record blowing；
Step 6：It is respectively t that access time, which is separated by shooting time,1And t2Two oil-film images, utilize image processing software and reason
Data processing is carried out by analysis method.
5. a kind of experimental method of hypersonic oil film interferometry frictional resistance measurement experiment device as described in claim 1, special
Sign is：Oil film interference friction resistance coefficient calculation formula：
N in formula Chinese style0Indicate the refractive index of silicone oil, θ indicates refraction angle, and it is total that Δ x indicates that N grades of stripeds move between two moment
Distance, N represent the fringe order of calculating, and λ indicates the wavelength for the monochromatic sodium vapor lamp selected in test, t1And t2Respectively represent oil film
Pattern shooting initial time and by moment, q∞(t) incoming flow dynamic pressure is indicated, μ (t) indicates to test silicone oil different moments used
Dynamic viscosity coefficient,.
6. a kind of experimental method of hypersonic oil film interferometry frictional resistance measurement experiment device as claimed in claim 13, special
Sign is：Δ x indicates the total distance that N grades of stripeds move between two moment：
Δ x=Δ x (t2)-Δx(t1)
Wherein Δ x (t1) and Δ x (t2) respectively represent t1And t2The N grade oil film fringe spacing at moment.
7. a kind of experimental method of hypersonic oil film interferometry frictional resistance measurement experiment device as claimed in claim 13, special
Sign is：Dynamic pressure q∞Calculating use compressible flow Bernoulli equation：
In conjunction with one dimensional isentropic flow basic relational expression：
Derive dynamic pressure q∞Calculating formula：
γ represents the specific heat ratio of air in formula, is constant 1.4 in experiment；M represents experiment Mach number, Ma=5；p0And ρ0Generation respectively
Table stagnation pressure and gross density, p and ρ represent static pressure and quiet density.Wherein p0It is set as 5 atmospheric pressure.
8. a kind of experimental method of hypersonic oil film interferometry frictional resistance measurement experiment device as described in claim 1-3,
Feature in：μ (t) indicates to test the dynamic viscosity coefficient of silicone oil different moments used, according to the temperature-of the analysis level silicone oil
Dynamic viscosity Coefficient Fitting curve obtains t in conjunction with the temperature that the thermocouple measures1And t2The dynamic viscosity of moment oil film
Coefficient.
9. a kind of experimental method of hypersonic oil film interferometry frictional resistance measurement experiment device as claimed in claim 13, special
Sign is：The parameter of above-mentioned acquisition is brought into coefficient of frictional resistance calculation formula, the friction of model surface measurement point is acquired
Resistance coefficient.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810453837.XA CN108918078A (en) | 2018-05-14 | 2018-05-14 | A kind of hypersonic oil film interferometry frictional resistance measurement experiment device and experimental method |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810453837.XA CN108918078A (en) | 2018-05-14 | 2018-05-14 | A kind of hypersonic oil film interferometry frictional resistance measurement experiment device and experimental method |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108918078A true CN108918078A (en) | 2018-11-30 |
Family
ID=64403454
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810453837.XA Pending CN108918078A (en) | 2018-05-14 | 2018-05-14 | A kind of hypersonic oil film interferometry frictional resistance measurement experiment device and experimental method |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108918078A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110646161A (en) * | 2019-11-01 | 2020-01-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Measured object surface treatment method for oil film interference measurement |
| CN112880966A (en) * | 2021-01-08 | 2021-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Fluorescent oil film thickness obtaining method based on CFD numerical simulation calculation |
| CN112964184A (en) * | 2021-04-12 | 2021-06-15 | 西华大学 | Oil film thickness measuring device and measuring method based on surface friction resistance experiment |
| CN116952525A (en) * | 2023-09-20 | 2023-10-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Non-contact measurement method and system for friction resistance of wing-shaped wall surface for wind tunnel experiment |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1819300A (en) * | 2004-09-17 | 2006-08-16 | 株式会社半导体能源研究所 | Light-emitting device |
| CN101654571A (en) * | 2009-08-21 | 2010-02-24 | 长兴（广州）精细涂料有限公司 | UV-curable colored paint composition |
| CN103981317A (en) * | 2014-05-30 | 2014-08-13 | 中南大学 | Blast furnace tapping hole molten iron temperature continuous detection method based on temperature drop model |
| CN104697705A (en) * | 2015-03-19 | 2015-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method of measuring friction stress on interference surface of oil film |
| CN106752583A (en) * | 2016-12-22 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of porous type simple component fast-response pressure sensitive coating formula and compound method |
| CN107202746A (en) * | 2017-06-29 | 2017-09-26 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of model surface frictional resistance measurement apparatus |
| CN108007668A (en) * | 2017-11-25 | 2018-05-08 | 南京航空航天大学 | A kind of swept-back wing three dimensional boundary layer frictional resistance measuring device and measuring method |
-
2018
- 2018-05-14 CN CN201810453837.XA patent/CN108918078A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1819300A (en) * | 2004-09-17 | 2006-08-16 | 株式会社半导体能源研究所 | Light-emitting device |
| CN101654571A (en) * | 2009-08-21 | 2010-02-24 | 长兴（广州）精细涂料有限公司 | UV-curable colored paint composition |
| CN103981317A (en) * | 2014-05-30 | 2014-08-13 | 中南大学 | Blast furnace tapping hole molten iron temperature continuous detection method based on temperature drop model |
| CN104697705A (en) * | 2015-03-19 | 2015-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method of measuring friction stress on interference surface of oil film |
| CN106752583A (en) * | 2016-12-22 | 2017-05-31 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of porous type simple component fast-response pressure sensitive coating formula and compound method |
| CN107202746A (en) * | 2017-06-29 | 2017-09-26 | 中国空气动力研究与发展中心超高速空气动力研究所 | A kind of model surface frictional resistance measurement apparatus |
| CN108007668A (en) * | 2017-11-25 | 2018-05-08 | 南京航空航天大学 | A kind of swept-back wing three dimensional boundary layer frictional resistance measuring device and measuring method |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110646161A (en) * | 2019-11-01 | 2020-01-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Measured object surface treatment method for oil film interference measurement |
| CN110646161B (en) * | 2019-11-01 | 2020-12-22 | 中国空气动力研究与发展中心高速空气动力研究所 | Measured object surface treatment method for oil film interference measurement |
| CN112880966A (en) * | 2021-01-08 | 2021-06-01 | 中国空气动力研究与发展中心高速空气动力研究所 | Fluorescent oil film thickness obtaining method based on CFD numerical simulation calculation |
| CN112964184A (en) * | 2021-04-12 | 2021-06-15 | 西华大学 | Oil film thickness measuring device and measuring method based on surface friction resistance experiment |
| CN112964184B (en) * | 2021-04-12 | 2022-07-01 | 西华大学 | Oil film thickness measuring device and measuring method based on surface friction resistance experiment |
| CN116952525A (en) * | 2023-09-20 | 2023-10-27 | 中国空气动力研究与发展中心低速空气动力研究所 | Non-contact measurement method and system for friction resistance of wing-shaped wall surface for wind tunnel experiment |
| CN116952525B (en) * | 2023-09-20 | 2023-12-01 | 中国空气动力研究与发展中心低速空气动力研究所 | Non-contact measurement method and system for friction resistance of wing-shaped wall surface for wind tunnel experiment |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN108918078A (en) | A kind of hypersonic oil film interferometry frictional resistance measurement experiment device and experimental method | |
| Goldhahn et al. | The background oriented schlieren technique: sensitivity, accuracy, resolution and application to a three-dimensional density field | |
| Kähler | Investigation of the spatio-temporal flow structure in the buffer region of a turbulent boundary layer by means of multiplane stereo PIV | |
| Sartor et al. | PIV study on a shock-induced separation in a transonic flow | |
| Duncan et al. | Effects of step excrescences on a swept wing in a low-disturbance wind tunnel | |
| Vinuesa et al. | Measurement of wall-shear stress | |
| Hartmann et al. | Tomographic background oriented schlieren applications for turbomachinery | |
| Han et al. | Applicability of Taylor’s hypothesis for estimating the mean streamwise length scale of large-scale structures in the near-neutral atmospheric surface layer | |
| Murphree et al. | Physics of unsteady cylinder-induced shock-wave/transitional boundary-layer interactions | |
| Zuccher et al. | Infrared thermography investigations in transitional supersonic boundary layers | |
| von Hoesslin et al. | Temperature decline thermography for laminar–turbulent transition detection in aerodynamics | |
| Gluzman et al. | A simplified photogrammetry procedure in oil-film interferometry for accurate skin-friction measurement over arbitrary geometries | |
| Goldhahn et al. | Quantitative measurements of three-dimensional density fields using the background oriented schlieren technique | |
| Ota et al. | Quantitative density measurement of the lateral jet/cross-flow interaction field by colored-grid background oriented schlieren (CGBOS) technique | |
| Alhaj et al. | Optical investigation of profile losses in a linear turbine cascade | |
| Zhao et al. | Measurement of surface shear stress vector distribution using shear-sensitive liquid crystal coatings | |
| Desse et al. | Shadow, Schlieren and Color Interferometry. | |
| Zanoun et al. | Three measuring techniques for assessing the mean wall skin friction in wall-bounded flows | |
| CN109059745A (en) | Capacitance sensor calibration method and apparatus for oil film thickness measurement | |
| Liu et al. | Experimental fluid mechanics | |
| Henderson | Crossflow transition at Mach 6 on a cone at low angles of attack | |
| Madad et al. | Skin friction measurement in zero and adverse pressure gradient boundary layers using oil film interferometry | |
| Davy et al. | Surface Flow Measurements of Supersonic Micro-Impinging Jets | |
| Yun et al. | Evolution of wall flow structure and measurement of shear stress issuing from supersonic jet with extended shelf | |
| Naughton et al. | Viscous Drag Measurements on Non-Smooth Surfaces |
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 | ||
| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20181130 |