CN108225717A - Flow resistance force measuring method in a kind of wind tunnel test - Google Patents
Flow resistance force measuring method in a kind of wind tunnel test Download PDFInfo
- Publication number
- CN108225717A CN108225717A CN201711361527.7A CN201711361527A CN108225717A CN 108225717 A CN108225717 A CN 108225717A CN 201711361527 A CN201711361527 A CN 201711361527A CN 108225717 A CN108225717 A CN 108225717A
- Authority
- CN
- China
- Prior art keywords
- pressure
- outlet
- flow passage
- flow resistance
- measurement
- 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.)
- Granted
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
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The present invention is a kind of method suitable for carrying out high-acruracy survey to flow resistance power in aircraft wind-tunnel, belongs to wind-tunnel technique field.The present invention utilizes the deficiency of flow resistance power technology acuracy in pipe amount of flow measure of the change for tradition, it proposes flow resistance force measuring method in a kind of novel high-precision, is measured including outlet three dimensional velocity vectors field PIV, static pressure-stagnation pressure blanket type measurement and three steps of Data Post are harrowed in removable pressure measurement.The cross section three dimensional velocity vectors field of inner flow passage outlet is accurately obtained using PIV measuring techniques, the boundary boundary of interior outflow can be accurately distinguished open, the measured value of stagnation pressure/static probe is modified using three dimensional velocity vectors angle.Mechanism is harrowed by the controllable pressure measurement of movement and carries out blanket type scanning pressure measurement, the stagnation pressure in inner flow passage outlet region, the data acquisition density of static pressure measurement point, the comprehensive precision for promoting flow resistance force measuring method in entire in terms of test data information content and data correction greatly improved.
Description
Technical field
The present invention is a kind of method suitable for carrying out high-acruracy survey to flow resistance power in aircraft wind-tunnel, belongs to wind
Hole experimental technique field.
Background technology
Flow resistance power is closely related with aircraft entirety aerodynamic characteristic in aircraft, and the precision measured directly affects flight
Device aeroperformance is assessed.Meanwhile with the raising of flight Mach number (Ma), engine is continuously increased with respect to cabinet size, entirely
Full machine ratio constantly rises shared by inner flow passage resistance, and therefore, how flow resistance power has the development of aircraft in high-acruracy survey
More and more important meaning and value.
Flow resistance force measuring method mainly has three categories in wind tunnel test at present：First, in model and balance design using several
What upper contactless design philosophy, inner flow passage and balance are connected directly, at the same keep on inner flow passage and model it is other therewith
Connected components incomplete contact between, intermediate space are closed using sealing material, then directly carry out dynamometry to inner flow passage using balance,
So as to obtain interior flow resistance power.Second is that directly its static pressure distribution is obtained, by arranging pressure tap on interior runner tube wall so as to indirectly
It calculates and measures flow resistance power in ventilating model.Determine flow resistance power in ventilating model third, changing according to pipe amount of flow, i.e., by
Close to inner flow passage outlet port arrangement pressure measurement rake, the momentum and average pressure in the section are measured, it is then poor using momentum is imported and exported
Wait flow resistance power in formula scales acquisition.
In above-mentioned three classes in flow resistance force measuring method, first method can theoretically reach a day sane level error precision,
But easily caused the Interaction Force of inner flow passage caused by model flexible deformation and model connected components by aerodynamic loading
Influence, particularly with the complex model of the asymmetric inner flow passage influence more very, skill is isolated to balance design and inside and outside flow pattern face
Art proposes quite high challenge.In addition, interior flow pattern face at the sealed connection on shape moulding surface structure always in the presence of can not disappear
The problems such as slit and finish for removing, the boundary layer flow dynamic characteristic near internal flow channel entry point are affected.Especially in incoming
When Mach number is higher, flowing similarity simulation certain deviation will occur, while to seal request higher, otherwise can introduce new
Aerodynamic loading error.Second method is primarily limited to the influence of the layout density of pressure tap on inner flow passage tube wall and can not obtain
High-precision interior flow resistance power, such as the limitation of model wall thickness can not arrange pressure tap, in inner flow passage complexity near zones such as leading edges
Curved surface nearby is also difficult to effectively arrange pressure tap etc..The third method can not only measure interior flow resistance power, also incidentally be flowed
Enter the flow of inner flow passage, there is higher meaning to performance evaluations such as aircraft propulsions.But the measurement accuracy of this method by
Total caused by air flow vector direction in front of exit pressure measurement rake arrangement quantity, inside/outside stream boundary definition and pressure-measuring probe/
The serious restriction of static pressure measurement error, there is an urgent need for exploring novel measuring method, to meet engineer application demand.
With the fields such as material, electronics, optics items new technology appearance and be constantly progressive, FLOW VISUALIZATION in wind tunnel test
Technology also gradually development therewith.Wherein, Particle Image Velocimetry (PIV) can follow fluid to move together using tracer, root
According to the light scattering of tracer or exciting characteristic analysis flow field structure, quantitative multi-parameter information of flow can be obtained, such as density, temperature
Degree, pressure, component and speed measurement of full field.Meanwhile the planar laser scattering system (NPLS) based on nano-particle can be preferable
Solving the problems, such as that tracing particle difference that existing high Ma numbers flow imaging technology faced and signal-to-noise ratio are low, technology is more mature,
And engineering adaptability is strong.It is contemplated that it is improved in wind-tunnel using the internal flow resistance power measuring technique of the system, so as to obtain more
High-precision interior flow resistance force measuring method.In recent years, carry out Primary Study and achieved certain achievement, but mainly use two
Dimension PIV technologies measure the longitudinal cross-section velocity field that different inner flow passages export and arrange that a large amount of total pressure probes are surveyed in outlet
The modes such as amount rake, since pressure measurement rake number of probes is limited and pressure measurement errors caused by air-flow drift angle and inside and outside outflux
The problems such as boundary accurate is distinguished is still unresolved, needs to be explored new test method and conducts a research.
Invention content
The purpose of the present invention, using the deficiency of flow resistance power technology acuracy in pipe amount of flow measure of the change, proposes one for tradition
Flow resistance force measuring method in kind novel high-precision, can more effectively measure flow resistance power in aircraft.
The measuring method of institute of the invention mainly includes that outlet three dimensional velocity vectors field PIV is measured, removable pressure measurement is harrowed
Static pressure-stagnation pressure blanket type measures and three step compositions of Data Post, is as follows：
First, to flowing the ventilating model of drag measurement in wind tunnel test using the outflow internal runner exit of PIV measuring methods
Outlet speed accurately measured, obtain the three dimensional velocity vectors field data of outlet
Then, blanket type measurement is carried out to outlet using the removable pressure measurement rake mechanism of electric cylinder control, obtained every
The static pressure and stagnation pressure of a measurement point greatly improve the data acquisition density of outlet.Meanwhile with reference to the air-flow of each measurement point
Azimuth, which carries out the stagnation pressure and static pressure measurement of the measurement point, to be corrected, and obtains the outlet pressure Distribution value of higher precision；
Finally, using based on mass flow averaging method, to outlet speed, static pressure, the data such as stagnation pressure obtained
It is handled, and interior flow resistance power D is obtained according to resistance calculation formulae is flowed in typical casen, specific derivation and calculating process are as follows：
Ventilating model exports the resistance relative to inner flow passage inlet upstream：
D∞=qm,∞v∞-qm,2v2+P∞A∞-P2A2 (1)
Ventilating model exports the resistance relative to inner flow passage entrance：
D1=qm,1v1-qm,2v2+P1A1-P2A2 (2)
Wherein, footmark ∞ refers to the remote front of inner flow passage inlet upstream, and footmark 1 refers to inner flow passage entry position, and footmark 2 refers to
Inner flow passage outlet port, qm,∞It is the mass flow in the remote front of inner flow passage inlet upstream, v∞It is the remote front of inner flow passage inlet upstream
Air velocity, qm,2Be inner flow passage outlet mass flow, v2Be inner flow passage outlet air velocity, P∞It is on inner flow passage entrance
The pressure in the remote front of trip, A∞It is the sectional area of the remote front flow tube of inner flow passage inlet upstream, P2Be inner flow passage outlet pressure, A2It is
The sectional area of inner flow passage outlet, qm,1It is the mass flow of inner flow passage entrance, v1It is the air velocity of inner flow passage entrance, P1It is interior stream
The pressure of road entrance, A1It is the sectional area of inner flow passage entrance.
Do not consider overflow, the q according to mass flow conservationm,∞=qm,1=qm,2, in addition, the gas in remote front and inlet
Stream is usually uniform and identical with test chamber environment, can be directly obtained from wind tunnel operation parameter.
It provides coordinate system, is moved according to the lateral arrangement measurement point sum ns (variable i) for measuring rake and along outlet
Shift position sum nt (the variable j), the mass flow q in exit in directionm,2Can discrete be：
The close region averag density of respectively each measurement point (i, j), area and along resistance
The axial velocity value in direction.
According to velocity vectorReferred to asAlong the axial velocity value of drag direction
WhereinFor the velocity space azimuth at each measurement point position in outlet,To survey
The angle with drag direction that the air flow vector of amount point (i, j) obtains after conversion；
According to typical gas dynamic theory formula：
Wherein, constant R=287.053N ﹒ m/ (Kg ﹒ K)
Wherein, T0For wind-tunnel total temperature, it is known that γ is specific heat ratio 1.4 during operation,For each measurement point (i, j)
Mach number,
Wherein, the stagnation pressure of measurement point (i, j)And static pressureIt needs to combine measurement point air flow vector and pressure-measuring probe
Between angle and front speed to actually measured valueWithIt is modified.Stagnation pressure and static pressure correction factorWithInterpolation is fitted by pre-stage test data to obtain,
I.e.：
Arrangement can obtain：
In addition, according to theoretical formula, since total temperature is certain, it can also in addition be derived by static pressure, density aerodynamic parameter
Relational expression between stagnation pressure and absolute velocity values is as follows：
Contrast equation (11) and (13), formula (12) and (14), respectively as measurement point (i, j) arbitrary on outlet
Static pressure and density two kinds of expression-forms, can corroborate each other.
Since total pressure measurement is smaller to the susceptibility of air-flow angle, error is relatively low, and revised value is more accurate,
Therefore local static pressure and density value will be based on formula (13) and (14), and formula (13) and (14) are only used as reduced value.At this point, root
It can be obtained according to formula (3), the aggregated momentum on entire inner flow passage outlet is represented by：
In addition, each aerodynamic parameter average value in ventilating model inner flow passage outlet has following result：
v2Mass flow weighted mean velocity (drag direction) for exit：
P2Mass flow weighted average static pressure for exit：
ρ2Mass flow weighted average density for exit：
Summary is various, by ventilating model outlet relative to the resistance D of inner flow passage inlet upstream∞It is set in wind tunnel test
Flow resistance power Dn, can obtain ventilating model outlet according to interior flow resistance power formula (1) is relative to the resistance in remote front：
From above formula it is found that being wind tunnel operation known parameters or can pass through for carrying out the items that interior flow resistance power calculates in detail
Measured static temperature, static pressure and three dimensional velocity vectors equivalence is calculated according to formula (3) ￣ (18).
Since each measured data precision is higher, respective data collecting system error magnitude, while profit can be reached
Inside and outside flow point circle boundary is can accurately measure out with PIV technologies, thus quite high-precision interior stream drag force measurement can be obtained.
The advantage of the invention is that：
1) the cross section three dimensional velocity vectors field of inner flow passage outlet is accurately obtained using PIV measuring techniques, it can accurate area
The boundary boundary outflowed in separating, and the measured value of stagnation pressure/static probe is modified using three dimensional velocity vectors angle, data
Precision greatly improves；
2) mechanism is harrowed by the controllable pressure measurement of movement and carries out blanket type scanning pressure measurement, inner flow passage outlet area greatly improved
The stagnation pressure in domain, the data acquisition density of static pressure measurement point, theoretically can be in same train number to outlet any position point
Aerodynamic data is acquired；
3) more accurately parameters such as rate of discharge, momentum are obtained using mass flow weighted average method；
4) the comprehensive precision for promoting flow resistance force measuring method in entire in terms of test data information content and data correction.
Description of the drawings
Fig. 1 is that the wind tunnel test of outflux momentum accurately measures overall plan schematic diagram in the present invention,
Fig. 2 is outlet static pressure/accurate instrumentation plan of pressure distribution.
1- ventilating models
2- side wall polishings region
3- inner flow passages export
4- total pressure measurement probe arrays
5- TRAJECTORY CONTROL sliding rails
6- static pressure measurement probe arrays
Support arm is harrowed in 7- pressure measurement
8- electric cylinders
9- model support seats
10- wind-tunnel tulwar connectors
11- measurement point coordinate systems
12- measurement point velocity vectors
Specific embodiment
With reference to Fig. 1 and Fig. 2, following embodiment is provided, implementer's case of the present invention is described further.
The ventilating model 1 of stream drag measurement is installed in wind-tunnel in typical, and ventilating model 1 is mounted on model support seat 9,
Model support seat 9 is connect with wind-tunnel tulwar connector 10.TRAJECTORY CONTROL sliding rail 5 is fixedly mounted on model support seat 9, pressure measurement rake
Support arm 7 can be moved in TRAJECTORY CONTROL sliding rail 5 by the driving of electric cylinder 8.It is pressure measurement in the free end of pressure measurement rake support arm 7
Rake, pressure measurement, which is harrowed, is equipped with pressure measurement rake total pressure measurement probe array 4 and pressure measurement rake static pressure measurement probe array 6.
(1) in the side wall polishing region 2 of wind-tunnel by laser polishing, the piece light of formation is close to inner flow passage outlet 3 as possible
Section, with ensure obtain be close to inner flow passage outlet 3 aerodynamic parameter.Wind-tunnel is run, after stablizing after flow field, in test chamber
Upstream persistently sows nano-particle and carries out PIV measurements, using the movement rail of the nano-particle near the internal runner exit 3 of camera
Mark is shot, and since laser sheet optical has certain thickness (being more than 1mm), thus can accurately obtain and own in inner flow passage outlet 3
The three dimensional velocity vectors field of particle (error is less than 0.5%)；
(2) after the velocity vector field PIV of inner flow passage outlet 3 is measured, electric cylinder 8 is controlled, along TRAJECTORY CONTROL sliding rail 5
Pressure measurement rake blanket type on light path plane is moved, measures stagnation pressure and static pressure distribution in inner flow passage outlet 3.Data acquire density
It can be given according to wind tunnel operation time and outlet size.In wind-tunnel starting process, pressure measurement rake is moved to from interior stream
Road exports 3 remote positions, avoids damaging pressure measurement rake because model shakes, after stablizing after wind-tunnel starting flow field, profit
Pressure measurement rake is controlled with electric cylinder 8 to measure the stagnation pressure of inner flow passage outlet 3 and static pressure distribution.Pressure measurement rake is given as two rows of surveys in Fig. 1
Probe is pressed, first row is total pressure measurement probe array 4, and second row is static pressure measurement probe array 6, and arrangement spacing is sprayed with inner flow passage
The pelvic outlet plane angle of pipe 3, probe diameter and to avoid static probe related to the interference of air-flow in front of total pressure probe.In addition,
The stagnation pressure of each measurement point (i, j)And static pressurePass through the air velocity at the position and air flow vector and pressure measurement
Angle between probe measures stagnation pressure to practicalStatic pressure is measured with practicalIt is modified, specific correction factorWithInterpolation is fitted by routine tests data early period to obtain
It arrives.
(3) using based on mass flow averaging method, to obtained outlet speed, stagnation pressure, the data such as static pressure into
Row processing, is calculated by the following formula：
Wherein,
AndThree
A main multinomial can be calculated by the measured data of PIV and pressure measurement rake, remainingP∞, ρ∞, v∞Etc. parameters be pressure measurement
Aerodynamic parameter during rake probe spacing geometric dimension and wind tunnel operation in test section is known.
Claims (8)
1. a kind of flow resistance force measuring method in wind tunnel test, it is characterised in that：This method includes outlet three dimensional velocity vectors
Field PIV is measured, static pressure-stagnation pressure blanket type measurement and three steps of Data Post are harrowed in removable pressure measurement, in Data Post
It is middle to use based on mass flow averaging method, the outlet speed, static pressure, the stagnation pressure data that are obtained are handled, and pressed
Interior flow resistance power D is obtained according to resistance calculation formulae is flowed in typical casen：
Dn=D∞=qm,∞v∞-qm,2v2+P∞A∞-P2A2
Wherein, qm,∞It is the mass flow in the remote front of inner flow passage inlet upstream, v∞It is the gas velocity in the remote front of inner flow passage inlet upstream
Degree, qm,2Be inner flow passage outlet mass flow, v2Be inner flow passage outlet air velocity, P∞It is before inner flow passage inlet upstream is remote
The pressure of side, A∞It is the sectional area of the remote front flow tube of inner flow passage inlet upstream, P2Be inner flow passage outlet pressure, A2It is inner flow passage
The sectional area of outlet.
2. flow resistance force measuring method in wind tunnel test according to claim 1, it is characterised in that：In the three-dimensional speed in outlet
When spending vector field PIV measurements, essence is carried out to the outlet speed that ventilating model inner flow passage exports using outflow PIV measuring methods
Locating tab assembly obtains the three dimensional velocity vectors field data of outlet
3. flow resistance force measuring method in wind tunnel test according to claim 2, it is characterised in that：It is harrowed in removable pressure measurement quiet
When pressure-stagnation pressure blanket type measures, according to the lateral arrangement measurement point i for measuring rake(i=1 ..., ns), along outlet movable direction
Shift position j(j=1 ... nt), obtain the measurement stagnation pressure of each measurement point (i, j)With measurement static pressureAnd it combines every
Angle and speed between the air flow vector and pressure-measuring probe of a measurement point (i, j) is to the measurement stagnation pressure of measurement point (i, j) and survey
It measures static pressure and carries out amendment, obtain the stagnation pressure of measurement point (i, j)And static pressure
For stagnation pressure correction factor,For static pressure correction factor,
Interpolation is fitted by pre-stage test data to obtain.
4. flow resistance force measuring method in wind tunnel test according to claim 3, it is characterised in that：qm,∞=qm,2, quality stream
Measure qm,2Can discrete be：
The close region averag density of respectively each measurement point (i, j), area and along drag direction
Axial velocity value.
5. flow resistance force measuring method in wind tunnel test according to claim 4, it is characterised in that：According to velocity vectorAlong the axial velocity value of drag direction
The angle with drag direction that air flow vector for measurement point (i, j) obtains after conversion.
6. flow resistance force measuring method in wind tunnel test according to claim 5, it is characterised in that：
Wherein, constant R=287.053N ﹒ m/ (Kg ﹒ K), T0For wind-tunnel total temperature, it is known that γ is specific heat ratio 1.4 during operation.
7. flow resistance force measuring method in wind tunnel test according to claim 6, it is characterised in that：The air-flow of inner flow passage outlet
Speed v2, the mass flow weighted mean velocity for drag direction：
The pressure P of inner flow passage outlet2, the mass flow weighted average static pressure for exit：
ρ2Mass flow weighted average density for exit：
8. flow resistance force measuring method in wind tunnel test according to claim 7, it is characterised in that：
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711361527.7A CN108225717B (en) | 2017-12-15 | 2017-12-15 | Measuring method for internal flow resistance in wind tunnel test |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711361527.7A CN108225717B (en) | 2017-12-15 | 2017-12-15 | Measuring method for internal flow resistance in wind tunnel test |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108225717A true CN108225717A (en) | 2018-06-29 |
| CN108225717B CN108225717B (en) | 2020-04-28 |
Family
ID=62649719
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711361527.7A Active CN108225717B (en) | 2017-12-15 | 2017-12-15 | Measuring method for internal flow resistance in wind tunnel test |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108225717B (en) |
Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110455491A (en) * | 2019-09-11 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | Interior flow resistance force measuring method and device based on bellows balance system |
| CN111537183A (en) * | 2020-05-19 | 2020-08-14 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN111551339A (en) * | 2020-04-28 | 2020-08-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Design method of special pressure measuring rake for deformed flow channel of wing-body fusion aircraft ventilation model |
| CN111766039A (en) * | 2020-07-10 | 2020-10-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel |
| CN111780949A (en) * | 2020-07-10 | 2020-10-16 | 南京航空航天大学 | CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment |
| CN112729853A (en) * | 2020-12-24 | 2021-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting resistance of main engine air inlet of propeller aircraft |
| CN112880567A (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 | Boundary layer thickness measuring method |
| CN114061896A (en) * | 2021-11-17 | 2022-02-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for processing internal resistance measurement test data of lifting body ventilation model |
| CN114414192A (en) * | 2021-12-24 | 2022-04-29 | 上海理工大学 | Device and method for testing hydraulic performance of water inlet channel of water-jet propeller |
| CN114608785A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field |
| CN115219145A (en) * | 2022-08-01 | 2022-10-21 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel attack angle mechanism |
| CN115575074A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method |
| CN115575080A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for accurately measuring internal resistance of high-speed wind tunnel ventilation model |
| CN116147875A (en) * | 2023-04-23 | 2023-05-23 | 中国空气动力研究与发展中心空天技术研究所 | Anti-pollution plane laser generation device of miniature probing type air film |
| CN117890128A (en) * | 2024-03-14 | 2024-04-16 | 中汽研汽车检验中心（天津）有限公司 | Method for testing running resistance of heavy vehicle under any load |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3605603A1 (en) * | 1986-02-21 | 1987-08-27 | Audi Ag | Method for the aerodynamic investigation of vehicles which are flowed around and partially flowed through and are available as models reduced to scale |
| CN102749181A (en) * | 2012-07-19 | 2012-10-24 | 西北工业大学 | Wind tunnel test method on basis of momentum theory |
| WO2015029479A1 (en) * | 2013-08-27 | 2015-03-05 | 独立行政法人科学技術振興機構 | Fluid transition analysis device, fluid transition analysis method, and program |
| CN106289712A (en) * | 2016-10-14 | 2017-01-04 | 中国航天空气动力技术研究院 | A kind of inner flow passage resistance measurement method |
-
2017
- 2017-12-15 CN CN201711361527.7A patent/CN108225717B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3605603A1 (en) * | 1986-02-21 | 1987-08-27 | Audi Ag | Method for the aerodynamic investigation of vehicles which are flowed around and partially flowed through and are available as models reduced to scale |
| CN102749181A (en) * | 2012-07-19 | 2012-10-24 | 西北工业大学 | Wind tunnel test method on basis of momentum theory |
| WO2015029479A1 (en) * | 2013-08-27 | 2015-03-05 | 独立行政法人科学技術振興機構 | Fluid transition analysis device, fluid transition analysis method, and program |
| CN106289712A (en) * | 2016-10-14 | 2017-01-04 | 中国航天空气动力技术研究院 | A kind of inner flow passage resistance measurement method |
Non-Patent Citations (3)
| Title |
|---|
| 王泽江 等: "高超声速通气模型直接测力试验", 《航空学报》 * |
| 许晓斌 等: "通气模型内流道阻力直接测量技术", 《推进技术》 * |
| 黄湛 等: "DPIV技术在高超声速通气模型内阻测量中的应用", 《应用力学学报》 * |
Cited By (25)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110455491A (en) * | 2019-09-11 | 2019-11-15 | 中国航空工业集团公司沈阳空气动力研究所 | Interior flow resistance force measuring method and device based on bellows balance system |
| CN111551339B (en) * | 2020-04-28 | 2021-10-08 | 中国空气动力研究与发展中心高速空气动力研究所 | Design method of special pressure measuring rake for deformed flow channel of wing-body fusion aircraft ventilation model |
| CN111551339A (en) * | 2020-04-28 | 2020-08-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Design method of special pressure measuring rake for deformed flow channel of wing-body fusion aircraft ventilation model |
| CN111537183A (en) * | 2020-05-19 | 2020-08-14 | 刘祥 | Ventilation model internal resistance supporting and measuring system |
| CN111766039B (en) * | 2020-07-10 | 2022-04-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel |
| CN111780949A (en) * | 2020-07-10 | 2020-10-16 | 南京航空航天大学 | CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment |
| CN111766039A (en) * | 2020-07-10 | 2020-10-13 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for calculating measurement result of compressible fluid disturbance mode of subsonic wind tunnel |
| CN112729853A (en) * | 2020-12-24 | 2021-04-30 | 中国航空工业集团公司西安飞机设计研究所 | Method for correcting resistance of main engine air inlet of propeller aircraft |
| CN112880567A (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 | Boundary layer thickness measuring method |
| CN112880567B (en) * | 2021-01-08 | 2022-05-31 | 中国空气动力研究与发展中心高速空气动力研究所 | Boundary layer thickness measuring method |
| CN114061896A (en) * | 2021-11-17 | 2022-02-18 | 中国空气动力研究与发展中心超高速空气动力研究所 | Method for processing internal resistance measurement test data of lifting body ventilation model |
| CN114414192B (en) * | 2021-12-24 | 2024-03-01 | 上海理工大学 | Device and method for testing hydraulic performance of water inlet flow channel of water jet propeller |
| CN114414192A (en) * | 2021-12-24 | 2022-04-29 | 上海理工大学 | Device and method for testing hydraulic performance of water inlet channel of water-jet propeller |
| CN114608785A (en) * | 2022-05-10 | 2022-06-10 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field |
| CN114608785B (en) * | 2022-05-10 | 2022-07-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field |
| CN115219145A (en) * | 2022-08-01 | 2022-10-21 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel attack angle mechanism |
| CN115219145B (en) * | 2022-08-01 | 2022-12-06 | 中国航空工业集团公司沈阳空气动力研究所 | High-speed wind tunnel attack angle mechanism |
| CN115575074A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method |
| CN115575080A (en) * | 2022-12-09 | 2023-01-06 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for accurately measuring internal resistance of high-speed wind tunnel ventilation model |
| CN115575074B (en) * | 2022-12-09 | 2023-03-10 | 中国空气动力研究与发展中心高速空气动力研究所 | High-speed wind tunnel ventilation model internal resistance measurement uncertainty analysis method |
| CN115575080B (en) * | 2022-12-09 | 2023-03-24 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for accurately measuring internal resistance of high-speed wind tunnel ventilation model |
| CN116147875A (en) * | 2023-04-23 | 2023-05-23 | 中国空气动力研究与发展中心空天技术研究所 | Anti-pollution plane laser generation device of miniature probing type air film |
| CN116147875B (en) * | 2023-04-23 | 2023-06-16 | 中国空气动力研究与发展中心空天技术研究所 | Anti-pollution plane laser generation device of miniature probing type air film |
| CN117890128A (en) * | 2024-03-14 | 2024-04-16 | 中汽研汽车检验中心（天津）有限公司 | Method for testing running resistance of heavy vehicle under any load |
| CN117890128B (en) * | 2024-03-14 | 2024-05-31 | 中汽研汽车检验中心（天津）有限公司 | Method for testing running resistance of heavy vehicle under any load |
Also Published As
| Publication number | Publication date |
|---|---|
| CN108225717B (en) | 2020-04-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN207610835U (en) | Flow resistance force measuring device in a kind of wind tunnel test | |
| CN108225717A (en) | Flow resistance force measuring method in a kind of wind tunnel test | |
| Ostermann et al. | The interaction between a spatially oscillating jet emitted by a fluidic oscillator and a cross-flow | |
| Langston et al. | Three-dimensional flow within a turbine cascade passage | |
| CN103969022B (en) | A kind of hypersonic wind tunnel turbulivity indirect measurement method | |
| CN108254032A (en) | River ultrasonic wave time difference method method of calculating flux | |
| CN106837840B (en) | It is a kind of to be used for the fan-shaped cascade experiment system that stator blade aeroperformance is studied in Non-uniform Currents | |
| CN104596769A (en) | Real thrust measuring and calculating method for test run of aero-engine on indoor test bed | |
| CN106092495A (en) | The measuring method of aircraft body resistance in wind tunnel test | |
| Yapa et al. | Comparison of magnetic resonance concentration measurements in water to temperature measurements in compressible air flows | |
| CN114894423B (en) | Method for measuring and analyzing acoustic modal propagation characteristics of compressible fluid of subsonic wind tunnel | |
| CN106895807B (en) | A kind of river vegetation group wake zone measurement of length method | |
| Weclas et al. | Flow separation in the inlet valve gap of piston engines | |
| CN110455229A (en) | The measurement method of inlet air flow buret boundary layer thickness | |
| Hirt et al. | Development of a flow field for testing a boundary-layer-ingesting propulsor | |
| CN106644361A (en) | Simple method for measuring transonic wind tunnel test section space flow field symmetry | |
| Pietrzyk | Experimental study of the interaction of dense jets with a crossflow for gas turbine applications | |
| CN103063371B (en) | Intensive tube bundle weld detection device and detection method | |
| Zhang et al. | The Effect of Compound Angle on Nozzle Suction Side Film Cooling | |
| CN113720401A (en) | Open channel flow measurement system and method based on underwater particle velocity measurement | |
| Chemnitz et al. | A comparison of turbulence levels from PIV and CTA downstream of a low-pressure turbine cascade at high-speed flow conditions | |
| Buck et al. | Design and evaluation of a single passage test model to obtain turbine airfoil film cooling effectiveness data | |
| Yapa et al. | Quantitative MRI measurements of hot streak development in a turbine vane cascade | |
| CN110083902A (en) | A kind of temperature distortion map mimetic design method based on discrete series | |
| Flack et al. | Constituency measurements in the mixing region of a cross flow jet using a laser velocimeter |
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 |