CN107741313A - A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance - Google Patents
A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance Download PDFInfo
- Publication number
- CN107741313A CN107741313A CN201711232467.9A CN201711232467A CN107741313A CN 107741313 A CN107741313 A CN 107741313A CN 201711232467 A CN201711232467 A CN 201711232467A CN 107741313 A CN107741313 A CN 107741313A
- Authority
- CN
- China
- Prior art keywords
- jet pipe
- tunnel
- mach number
- section
- disturbance
- 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
- 238000011144 upstream manufacturing Methods 0.000 claims abstract description 36
- 238000010521 absorption reaction Methods 0.000 claims abstract description 13
- 238000013461 design Methods 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 12
- 229920000742 Cotton Polymers 0.000 claims description 10
- 230000008602 contraction Effects 0.000 claims description 7
- 230000008030 elimination Effects 0.000 claims description 6
- 238000003379 elimination reaction Methods 0.000 claims description 6
- 238000000034 method Methods 0.000 claims description 6
- 238000005086 pumping Methods 0.000 claims description 4
- CNKHSLKYRMDDNQ-UHFFFAOYSA-N halofenozide Chemical compound C=1C=CC=CC=1C(=O)N(C(C)(C)C)NC(=O)C1=CC=C(Cl)C=C1 CNKHSLKYRMDDNQ-UHFFFAOYSA-N 0.000 claims description 3
- 238000005192 partition Methods 0.000 claims description 3
- 230000003584 silencer Effects 0.000 claims description 3
- 230000000903 blocking effect Effects 0.000 claims 1
- 238000012360 testing method Methods 0.000 abstract description 10
- 238000013016 damping Methods 0.000 abstract description 3
- 230000006872 improvement Effects 0.000 abstract description 3
- 240000005528 Arctium lappa Species 0.000 abstract description 2
- 238000007664 blowing Methods 0.000 abstract description 2
- 238000002347 injection Methods 0.000 abstract description 2
- 239000007924 injection Substances 0.000 abstract description 2
- 238000010276 construction Methods 0.000 abstract 1
- 239000010410 layer Substances 0.000 description 21
- 230000000694 effects Effects 0.000 description 3
- 238000005243 fluidization Methods 0.000 description 3
- 230000035939 shock Effects 0.000 description 3
- 238000011161 development Methods 0.000 description 2
- 239000011229 interlayer Substances 0.000 description 2
- 230000001788 irregular Effects 0.000 description 2
- 239000002243 precursor Substances 0.000 description 2
- 230000007704 transition Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000010835 comparative analysis Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 239000000945 filler Substances 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 210000000867 larynx Anatomy 0.000 description 1
- 238000005259 measurement Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000010349 pulsation Effects 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 239000007921 spray Substances 0.000 description 1
- 230000009897 systematic effect Effects 0.000 description 1
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
- G01M9/02—Wind tunnels
- G01M9/04—Details
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 relates to High Mach number testing equipment, is related to a kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance, includes the low mach jet pipe of upstream High Mach number jet pipe, high-speed rectifier section and downstream belt boundary layer suction.Wherein, high-speed rectifier section is containing devices such as sound gobo, sound absorption section, honeycomb and damping screens.During wide Mach number operation, upstream jet pipe and high-speed rectifier section are shared, and operation Mach number and the matching of jet pipe size are realized by changing downstream jet pipe.The structure has three and shrinks venturi position (velocity of sound section), and upstream nozzle throat is limited flow section, and the throat area of downstream jet pipe is at least greater than upstream jet pipe, while the area is than determining total flow losses.Technical scheme only needs to do local flow improvement to the jet pipe of wind-tunnel, available for conventional bottom blowing type, injection type or blowdown-ejection wind tunnel, it can also be used to impulse wind tunnel, and because upstream High Mach number jet pipe is fixed, unified stable section or body size can be used, it is simple in construction, easy to operation.
Description
Technical field
The present invention relates to High Mach number testing equipment, is related to a kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance.
Background technology
The pulsation of test section incoming-flow pressure is generally higher by one up to 5% than practical flight environment in conventional High Mach number wind-tunnel
To two orders of magnitude, model aerodynamic force/thermal measurement is had a significant impact, particularly wall boundary layer flow state.Try
The comparative analysis for testing result and flying quality shows that test section background perturbation has a great influence to transition Reynolds number, and different wind-tunnel
Due to disturbing level existence difference, result of the test is inconsistent.
The disturbance that test chamber measures (is produced by the disturbance transmitted in room by damping screen, honeycomb, valve, pipeline etc.
It is raw), the random small whirlpool disturbance of jet pipe wall turbulent boundary layer etc. forms.Wherein, disturbance type mainly includes non-uniform temperature shape
Into " entropy spot " (also referred to as entropy wave), speed irregular fluctuation (turbulivity, also referred to as whirlpool ripple), pressure irregular fluctuation (acoustic disturbance/make an uproar
Sound, also referred to as sound wave).With the increase of jet pipe Mach number, wall at random strengthen by small whirlpool disturbing influence.
Reduce the random small whirlpool disturbance of jet pipe wall turbulent boundary layer, it is important to keep jet pipe wall side as long as possible
Interlayer laminar condition.One of important measures of Jing Yin jet pipe be jet pipe import eliminate stay room and contraction section wall boundary layer pair
The influence of jet pipe boundary layer flow, venturi front set aspirator, and a suction socket is constructed around venturi.
Carried out systematic development work for the research of Jing Yin jet pipe both at home and abroad, explore the suction of upstream edge interlayer, jet pipe type,
The factors such as expansion rate, wall curvature, barometric gradient, the wall angle of flex point, wall finish and cleannes are to orifice layer
The influence relation of fluidisation.But there is following limitation in existing design method：
On the one hand, due to blow-suction wind-tunnel inevitably supplies disturbance so that jet pipe size is smaller, operation is limited.Mesh
The hypersonic quiet wind tunnel of full-size is university of BeiJing, China M6 quiet wind tunnels on former world, nozzle exit diameter 0.3m；
On the other hand, as hypersonic aircraft develops the increase of demand, it is badly in need of High Mach number wind-tunnel and possesses perianal hertz
Number service ability.Suction effect and operation Mach number, nozzle area contraction ratio and running status are closely related, even if suction socket is designed to
Width is adjustable, and to meet different operation Reynolds number demands, but nozzle area contraction ratio is limited by stable section or pipe diameter, it is difficult to
Match wide Mach number service requirement.
Therefore, in the case where ensureing the precursor of jet pipe size, realize that wide range of Mach numbers internal layer fluidisation designing technique is needed into one
Step development.
The content of the invention
The present invention is directed to propose a kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance, is difficult to protecting to solve prior art
Demonstrate,prove under jet pipe size precursor, realize wide range of Mach numbers internal layer fluidisation design problem.
The concrete technical scheme of the present invention：A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance, it is characterised in that including
Upstream jet pipe 9, etc. straight section 11, downstream jet pipe 12, connected using form of flanges between each section, on the inner chamber of upstream jet pipe 9
It is close to include suction socket 5, downstream jet pipe larynx with the connection end of upstream wind-tunnel body 7, downstream jet pipe 12 provided with upstream nozzle throat 1
Road 6, suction socket 5 is located at the upstream of downstream nozzle throat 6, close with waiting connection end of straight section 11.
It is described to wait straight section 11 inner chamber to be connected successively from left to right noise elimination dividing plate 2, multiple layer metal net 10, sound absorption cotton 3, honeycomb
4。
The noise elimination dividing plate 2 is made up of two groups of silencers, is eliminated the noise respectively for high and low frequency noise, silencer exists
Deng straight section inner section congestion degree, between 40%~50%, the control of partition room channel velocity is in 30m/s or so, its profile
Smooth is streamlined, and head is semicircle, and afterbody is tapered pointed, and afterbody angle is 35 ° or so.
The multiple layer metal net 10, sound absorption cotton 3 form sound absorption section, and individual layer sound absorption cotton needs double layer of metal net spacing.
The multiple layer metal net 10, honeycomb 4, which are formed, eliminates whirlpool disturbance section, and honeycomb uses hexgonal structure, draw ratio
For 8 or so, be followed by first layer metal net, this layer of wire netting 30mesh/in, string diameter 160um.It is followed by wire netting net group,
Related to waiting straight section diameter away from choosing, parameter is chosen as 50mesh/in, string diameter 100um.
The upstream nozzle throat 1 is the annular projection in the inner chamber of upstream jet pipe 9.
The entrance Mach 2 ship 0.3 or so of suction socket 5, for pumping efficiency between 10% to 50%, suction conduit is big
Be advantageous to suppress to separate inside conduit in 90 ° of deflection angles.
The low wide Mach number wind-tunnel laminar flow double venturi of disturbance has three and shrinks velocity of sound section, and upstream nozzle throat is limited
Flow section, the throat area of downstream jet pipe is at least greater than upstream jet pipe, while the area is than determining total flow losses.
The upstream jet pipe 9 can use traditional " three-stage " Nozzle Design method, including subsonic speed contraction section, transonic speed section
With supersonic speed section.
Beneficial effects of the present invention：The laminar flow double venturi of the present invention is a kind of design in fixed face, passes through change
The design Mach number and discharge area of up/down trip jet pipe are than that can meet the needs of different.Technical scheme only needs
Local flow improvement is done to the jet pipe of wind-tunnel, available for conventional bottom blowing type, injection type or blows-draw formula wind-tunnel, it can also be used to pulsed wind
Hole, there is operability in practical implementation.The laminar flow double venturi of the present invention is in wide Mach number running without multiple
Miscellaneous start controlling organization, and because upstream High Mach number jet pipe is fixed, unified stable section or body size, structure can be used
Simply, reliably.
Brief description of the drawings
Fig. 1 is the low disturbance width Mach number wind-tunnel laminar flow double venturi schematic layout pattern of the present invention
Fig. 2 is that the jet pipe of the low disturbance width Mach number wind-tunnel laminar flow double venturi downstream belt suction socket of the present invention calculates grid
Fig. 3 is the low disturbance width Mach number wind-tunnel laminar flow double venturi suction socket local flow performance plot of the present invention
Fig. 4 is structure connection signal of the low disturbance width Mach number wind-tunnel laminar flow double venturi of the present invention in impulse wind tunnel
Figure.
Embodiment
As shown in figure 1, the wide Mach number wind-tunnel laminar flow double venturi scheme of low disturbance provided by the invention, upstream jet pipe 9 can be with
Wind-tunnel body 7 is directly connected to, and the downstream jet pipe 12 with suction socket 5 is used to produce the flow conditions for meeting experiment needs, two sections of sprays
Straight section 11 is waited to be used to reduce disturbance between pipe.
Program specific implementation design method is divided into the following aspects：
1) upstream and downstream parameters relationship
The Flows structures shape that the low wide Mach number wind-tunnel laminar flow double venturi flow losses of disturbance are occurred by inside, shock wave
The position that flows to of structure is determined by upstream nozzle throat 1, downstream nozzle throat 6 and suction groove area ratio.According to flow conservation, have
Following relational expression：
Wherein,For upstream nozzle throat area,For downstream nozzle throat area,To aspirate groove area, P10To be upper
Swim nozzle throat section stagnation pressure, P20For downstream nozzle throat section stagnation pressure.
2) noise elimination dividing plate
Noise elimination dividing plate 2 is used to eliminate acoustic disturbance in wide frequency range, along etc. the entrance of straight section 11 install two groups axially back and forth and disappear
Sound device, eliminated the noise respectively for high and low frequency noise.Silencer is waiting straight section inner section congestion degree, between 40%~50%
Between, for the control of partition room channel velocity in 30m/s or so, its profile is smoothly streamlined, and head is semicircle, and afterbody is tapered
Pointed, afterbody angle is 35 ° or so.
3) absorb sound section
The section that absorbs sound reduces noise by multiple layer metal net 10 and the grade of sound absorption cotton 3 filled therebetween.Individual layer sound absorption cotton needs two
Layer wire netting is spacing.Because the quality of sound absorbing capabilities is closely related with experimental condition, increase sound absorption cotton or metal need to be remained in advance
The space of net.By taking diameter 600mm grade straight section as an example：Four layer multi-layer wire nettings can be used, thickness is 0.64cm or so, and one layer is inhaled
Sound cotton filler；Headspace about 1000mm.
4) whirlpool disturbance section is eliminated
Designed in conjunction using honeycomb 4 and wire netting, honeycomb uses hexgonal structure, and draw ratio is 8 or so, afterwards
Meet first layer metal net, this layer of wire netting 30mesh/in, string diameter 160um.It is followed by wire netting net group, and spacing is chosen with waiting directly
Section diameter is related, and parameter is chosen as 50mesh/in, string diameter 100um.
5) suction socket
As shown in Fig. 2 the design of middle and lower reaches jet pipe suction socket 5 of the present invention, should in addition to it need to meet certain pumping efficiency
Avoid producing flow separation as far as possible, to prevent from disturbing forward pass interference test flow field.Result of study shows that suction conduit is more than
90 ° of deflection angle is advantageous to suppress to separate inside conduit.
As shown in figure 3, the low disturbance width Mach number wind-tunnel laminar flow double venturi of the present invention can be directly used in impulse wind tunnel, on
Trip is connected with driving body, and downstream is connected with test section.
The low disturbance width Mach number wind-tunnel laminar flow double venturi of the present invention may be directly applied to impulse wind tunnel, it can also be used to often
Advise in intermittent wind tunnel.Above example is only that a kind of parameter of the present invention chooses reference, is not intended to limit the present invention's
Protection domain, all within the principle of the present invention, any modification, replacement or improvement for being made etc., the protection in the present invention
Within the scope of.
Upstream High Mach number jet pipe plays metering function, there is provided meet the gas flow of certain stagnation temperature and total pressure request, can
Using traditional " three-stage " Nozzle Design method, including subsonic speed contraction section, transonic speed section and supersonic speed section.
High-speed rectifier section is used to eliminate low-and high-frequency disturbance, including rectification leading portion, rectification stage casing and rectification back segment.Wherein, it is whole
Flow leading portion and include sound gobo and sound absorption section, for reducing noise；Rectification stage casing, shape is combined using honeycomb and damping screen
Formula, for reducing whirlpool disturbance；Rectification back segment, for flow field nature transition, before being further lowered into downstream jet pipe contraction section
Total disturbance.
The low mach jet pipe of downstream belt boundary layer suction, which is used to provide, meets test Mach number and the flowing that disturbance requires
Environment, including supersonic speed section quasi spline, venturi nearby transonic speed section Profile Design and the Asia based on throat's boundary layer suction
Across super section/suction system integrated design.In order to ensure suction effect, suction socket entrance Mach 2 ship 0.3 or so, pumping efficiency
Between 10% to 50%.
During wide Mach number operation, upstream High Mach number jet pipe and high-speed rectifier section share, by changing downstream low mach
Jet pipe realizes operation Mach number and the matching of jet pipe size.
Especially, there is following flow performance under above-mentioned laminar flow double venturi working condition：
The up/down trip nozzle throat and suction socket venturi reach the velocity of sound simultaneously, the expansion segment after the nozzle throat of upstream
Inside with the presence of shock wave string structure, supersonic speed wave system fluidal texture be present in the leading portion of high-speed rectifier section and coupled with sound absorption loose structure
Effect.Pitot loss caused by shock train original position and coupling is determined by up/down trip nozzle throat area ratio.
In order to reach above-mentioned working condition, up/down trip nozzle throat area ratio should meet to require as follows：
Upstream nozzle throat is limited flow section, and the throat area of downstream jet pipe is at least greater than upstream nozzle throat area,
The limit for also needing to be less than its permission simultaneously takes area, the design Mach number and discharge area phase of the area and two jet pipes
Close.
Claims (9)
- A kind of 1. low wide Mach number wind-tunnel laminar flow double venturi of disturbance, it is characterised in that including upstream jet pipe (9), etc. straight section (11), Downstream jet pipe (12), connected using form of flanges between each section, upstream jet pipe (9) inner chamber is provided with upstream nozzle throat (1) it is, close to include suction socket (5), downstream nozzle throat (6) with upstream wind-tunnel body (7) connection end, downstream jet pipe (12), take out Bothrium (5) is located at downstream nozzle throat (6) upstream, close with waiting straight section (11) connection end.
- 2. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 1, it is characterised in that described to wait straight section (11) Inner chamber from left to right successively be connected noise elimination dividing plate (2), multiple layer metal net (10), sound absorption cotton (3), honeycomb (4).
- 3. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 2, it is characterised in that the noise elimination dividing plate (2) it is made up of two groups of silencers, is eliminated the noise respectively for high and low frequency noise, silencer is waiting the blocking of straight section inner section Degree, between 40%~50%, for the control of partition room channel velocity in 30m/s or so, its profile is smooth streamlined, head For semicircle, afterbody is tapered pointed, and afterbody angle is 35 ° or so.
- 4. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 2, it is characterised in that the multiple layer metal net (10) cotton (3) that, absorbs sound forms sound absorption section, and individual layer sound absorption cotton needs double layer of metal net spacing.
- 5. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 2, it is characterised in that the multiple layer metal net (10), honeycomb (4), which is formed, eliminates whirlpool disturbance section, and honeycomb use hexgonal structure, and draw ratio is 8 or so, be followed by first Layer wire netting, this layer of wire netting 30mesh/in, string diameter 160um.It is followed by wire netting net group, and spacing is chosen with waiting straight section diameter Correlation, parameter are chosen as 50mesh/in, string diameter 100um.
- 6. the low disturbance width Mach number wind-tunnel laminar flow double venturi as described in claim 1 to 5 any one, it is characterised in that institute It is the annular projection in upstream jet pipe (9) inner chamber to state upstream nozzle throat (1).
- 7. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 6, it is characterised in that the suction socket (5) Entrance Mach 2 ship 0.3 or so, between 10% to 50%, deflection angle of the suction conduit more than 90 ° is advantageous to pumping efficiency Suppress to separate inside conduit.
- 8. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 1, it is characterised in that the low wide horse of disturbance Conspicuous several wind-tunnel laminar flow double venturis have three and shrink velocity of sound sections, and upstream nozzle throat is limited flow section, the venturi of downstream jet pipe Area is at least greater than upstream jet pipe, while the area is than determining total flow losses.
- 9. the low wide Mach number wind-tunnel laminar flow double venturi of disturbance as claimed in claim 1, it is characterised in that the upstream jet pipe (9) traditional " three-stage " Nozzle Design method, including subsonic speed contraction section, transonic speed section and supersonic speed section can be used.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711232467.9A CN107741313A (en) | 2017-11-29 | 2017-11-29 | A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201711232467.9A CN107741313A (en) | 2017-11-29 | 2017-11-29 | A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN107741313A true CN107741313A (en) | 2018-02-27 |
Family
ID=61239756
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201711232467.9A Pending CN107741313A (en) | 2017-11-29 | 2017-11-29 | A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN107741313A (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108181076A (en) * | 2018-03-27 | 2018-06-19 | 中国人民解放军国防科技大学 | Wind tunnel for subsonic mixing layer |
| CN108709044A (en) * | 2018-05-23 | 2018-10-26 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of pressure piping flow rectifying silencer |
| CN110124409A (en) * | 2019-05-06 | 2019-08-16 | 沈阳航空航天大学 | A kind of DC low-speed wind-tunnel damping screen cleaning device |
| CN111006836A (en) * | 2019-12-16 | 2020-04-14 | 华中科技大学 | Tandem supersonic and hypersonic wind tunnel and flow stabilizing method thereof |
| CN111426445A (en) * | 2020-04-23 | 2020-07-17 | 空气动力学国家重点实验室 | Lodvichg wind tunnel and method for expanding high Mach number thereof |
| CN112665815A (en) * | 2020-12-28 | 2021-04-16 | 中国航天空气动力技术研究院 | Low-noise flow field debugging platform |
| CN113155400A (en) * | 2021-04-25 | 2021-07-23 | 华南理工大学 | Low-speed wind tunnel device |
| CN113270084A (en) * | 2021-05-12 | 2021-08-17 | 中国航空工业集团公司沈阳空气动力研究所 | Noise reduction device and method for aircraft cavity based on sound absorption material |
| CN115541169A (en) * | 2022-11-16 | 2022-12-30 | 中国航空工业集团公司沈阳空气动力研究所 | Superposed driving pipe wind tunnel compact quick-opening system and method |
| CN115824561A (en) * | 2023-02-22 | 2023-03-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of transition on dynamic characteristics of aircraft |
| CN117405351A (en) * | 2023-12-14 | 2024-01-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Advance pipe wind tunnel structure for reducing incoming flow noise |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1117244A (en) * | 1954-12-20 | 1956-05-18 | Snecma | Supersonic wind tunnel with variable number of machines |
| GB920079A (en) * | 1960-10-14 | 1963-03-06 | Bristol Siddeley Engines Ltd | Improvements in or relating to apparatus for producing a high velocity gaseous stream |
| CN103698100A (en) * | 2013-12-27 | 2014-04-02 | 中国人民解放军国防科学技术大学 | Ultrasonic wind tunnel and determining method thereof |
| CN104280205A (en) * | 2014-10-24 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof |
| CN207923408U (en) * | 2017-11-29 | 2018-09-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wide Mach number wind-tunnel laminar flow double venturi of low disturbance |
-
2017
- 2017-11-29 CN CN201711232467.9A patent/CN107741313A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| FR1117244A (en) * | 1954-12-20 | 1956-05-18 | Snecma | Supersonic wind tunnel with variable number of machines |
| GB920079A (en) * | 1960-10-14 | 1963-03-06 | Bristol Siddeley Engines Ltd | Improvements in or relating to apparatus for producing a high velocity gaseous stream |
| CN103698100A (en) * | 2013-12-27 | 2014-04-02 | 中国人民解放军国防科学技术大学 | Ultrasonic wind tunnel and determining method thereof |
| CN104280205A (en) * | 2014-10-24 | 2015-01-14 | 中国人民解放军国防科学技术大学 | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof |
| CN207923408U (en) * | 2017-11-29 | 2018-09-28 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of wide Mach number wind-tunnel laminar flow double venturi of low disturbance |
Non-Patent Citations (2)
| Title |
|---|
| 高亮杰;钱战森;王璐;王彤;: "高马赫数低噪声风洞层流喷管设计与性能评估", 航空科学技术, no. 08, pages 72 - 82 * |
| 高亮杰等: "宽马赫数路德维希管风洞及其关键技术", 南京航空航天大学学报, vol. 49, pages 36 - 40 * |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108181076A (en) * | 2018-03-27 | 2018-06-19 | 中国人民解放军国防科技大学 | Wind tunnel for subsonic mixing layer |
| CN108709044A (en) * | 2018-05-23 | 2018-10-26 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of pressure piping flow rectifying silencer |
| CN110124409A (en) * | 2019-05-06 | 2019-08-16 | 沈阳航空航天大学 | A kind of DC low-speed wind-tunnel damping screen cleaning device |
| CN111006836A (en) * | 2019-12-16 | 2020-04-14 | 华中科技大学 | Tandem supersonic and hypersonic wind tunnel and flow stabilizing method thereof |
| CN111426445A (en) * | 2020-04-23 | 2020-07-17 | 空气动力学国家重点实验室 | Lodvichg wind tunnel and method for expanding high Mach number thereof |
| CN112665815B (en) * | 2020-12-28 | 2023-03-21 | 中国航天空气动力技术研究院 | Low-noise flow field debugging platform |
| CN112665815A (en) * | 2020-12-28 | 2021-04-16 | 中国航天空气动力技术研究院 | Low-noise flow field debugging platform |
| CN113155400A (en) * | 2021-04-25 | 2021-07-23 | 华南理工大学 | Low-speed wind tunnel device |
| CN113270084A (en) * | 2021-05-12 | 2021-08-17 | 中国航空工业集团公司沈阳空气动力研究所 | Noise reduction device and method for aircraft cavity based on sound absorption material |
| CN115541169A (en) * | 2022-11-16 | 2022-12-30 | 中国航空工业集团公司沈阳空气动力研究所 | Superposed driving pipe wind tunnel compact quick-opening system and method |
| CN115824561A (en) * | 2023-02-22 | 2023-03-21 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of transition on dynamic characteristics of aircraft |
| CN115824561B (en) * | 2023-02-22 | 2023-04-14 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test method for obtaining influence of transition on dynamic characteristics of aircraft |
| CN117405351A (en) * | 2023-12-14 | 2024-01-16 | 中国空气动力研究与发展中心计算空气动力研究所 | Advance pipe wind tunnel structure for reducing incoming flow noise |
| CN117405351B (en) * | 2023-12-14 | 2024-03-12 | 中国空气动力研究与发展中心计算空气动力研究所 | Advance pipe wind tunnel structure for reducing incoming flow noise |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN107741313A (en) | A kind of low wide Mach number wind-tunnel laminar flow double venturi of disturbance | |
| CN207923408U (en) | A kind of wide Mach number wind-tunnel laminar flow double venturi of low disturbance | |
| CN108168832B (en) | A kind of throat structure improving tube wind tunnel test Reynolds number | |
| CN108195544B (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN105667811A (en) | Design method for multi-stage coupling integrated structure of front body and air inflow channel of hypersonic aircraft | |
| CN104280205A (en) | Supersonic velocity laminar flow spraying pipe and supersonic velocity quiet wind tunnel thereof | |
| CN102218378B (en) | Ultrasonic nonuniform flow nozzle and design method thereof | |
| CN204495535U (en) | 1.2 meters of magnitude wind-tunnel represent dynamically injectors | |
| CN106015818B (en) | A kind of energy-saving silencing pipeline | |
| CN102023077A (en) | Supersonic velocity axisymmetrical boundary layer wind tunnel | |
| CN106596038B (en) | The calculation method of the mute wind tunnel nozzle suction flow of supersonic and hypersonic | |
| CN212903808U (en) | Ejector and wind tunnel test device with same | |
| CN203925778U (en) | The jet apparatus of turbofan engine | |
| CN103926050B (en) | Hypersonic quiet jet pipe and determine method | |
| CN115048753A (en) | Continuous transonic wind tunnel aerodynamic shape design method | |
| CN206190472U (en) | Gas attenuating device | |
| CN105570598A (en) | Pipe rectifying device | |
| CN106837601B (en) | Venturi offset fluidic vectoring nozzle with lateral expansion | |
| CN109353527A (en) | Using the BLI air intake duct of mixed flow control method | |
| CN113865878B (en) | Large-discharge-quantity waste gas silencing and discharging device and method for airplane engine driving test | |
| CN103678774B (en) | Designing method for supersonic velocity thrust exhaust nozzle considering inlet parameter unevenness | |
| CN108240898A (en) | A kind of impulse type wind-tunnel tandem jet pipe | |
| CN108759948A (en) | A kind of built-in rectifier of gas ultrasonic flowmeter | |
| CN110569547B (en) | Supersonic velocity spray pipe of plasma generator and design method thereof | |
| CN207122704U (en) | A kind of energy-saving silencing pipeline suitable for the vertical air intake in 90 ° of top |
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 |