CN206740354U - A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system - Google Patents
A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system Download PDFInfo
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- CN206740354U CN206740354U CN201720556502.1U CN201720556502U CN206740354U CN 206740354 U CN206740354 U CN 206740354U CN 201720556502 U CN201720556502 U CN 201720556502U CN 206740354 U CN206740354 U CN 206740354U
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- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 title claims abstract description 56
- 238000001816 cooling Methods 0.000 title claims abstract description 30
- 229910052757 nitrogen Inorganic materials 0.000 title claims abstract description 28
- 239000000523 sample Substances 0.000 claims abstract description 58
- 239000004020 conductor Substances 0.000 claims abstract description 15
- 238000009434 installation Methods 0.000 claims description 5
- 230000008602 contraction Effects 0.000 claims description 3
- 238000005259 measurement Methods 0.000 abstract description 7
- 238000012360 testing method Methods 0.000 description 14
- 239000007788 liquid Substances 0.000 description 9
- 238000002474 experimental method Methods 0.000 description 8
- 238000013461 design Methods 0.000 description 6
- 239000000463 material Substances 0.000 description 6
- 241000743339 Agrostis Species 0.000 description 4
- 229910001220 stainless steel Inorganic materials 0.000 description 4
- 239000010935 stainless steel Substances 0.000 description 4
- 238000009529 body temperature measurement Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 3
- 238000010276 construction Methods 0.000 description 2
- 230000007547 defect Effects 0.000 description 2
- 238000009826 distribution Methods 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 238000001704 evaporation Methods 0.000 description 2
- 230000008020 evaporation Effects 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 238000004861 thermometry Methods 0.000 description 2
- 241000208340 Araliaceae Species 0.000 description 1
- 235000005035 Panax pseudoginseng ssp. pseudoginseng Nutrition 0.000 description 1
- 235000003140 Panax quinquefolius Nutrition 0.000 description 1
- 238000010521 absorption reaction Methods 0.000 description 1
- 238000004458 analytical method Methods 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009835 boiling Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000002309 gasification Methods 0.000 description 1
- 235000008434 ginseng Nutrition 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000000465 moulding Methods 0.000 description 1
- 238000006902 nitrogenation reaction Methods 0.000 description 1
- 238000000926 separation method Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 238000012546 transfer Methods 0.000 description 1
- 238000009827 uniform distribution Methods 0.000 description 1
- 238000009834 vaporization Methods 0.000 description 1
- 230000008016 vaporization Effects 0.000 description 1
- 238000003466 welding Methods 0.000 description 1
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- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The utility model proposes a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system, including multiple temp probes, multiple probe pole, framed bent, base, end plate and data conductors；Temp probe is identical with probe pole number；Temp probe uses semiellipsoid profile, is installed on using threaded connection on probe pole, and the data conductor of temp probe is drawn by the central through hole of pop one's head in pole central through hole and framed bent；Multiple probe poles are along framed bent short transverse equidistantly distributed；Cross section of the framed bent along short transverse uses along tunnel airstream direction thick middle, front and rear narrow cross sectional shape, probe pole and is arranged on framed bent front end；Base upper end is fixedly connected with framed bent bottom, and lower end is fixedly installed in hole wall under wind-tunnel；Endplate root is fixedly connected at the top of framed bent, and hole wall on wind-tunnel is fixedly installed at the top of end plate.The utility model realizes the accurate measurement of wind-tunnel cooling system stagnation temperature, and technical support is provided to build up China's first set continuous high-speed wind-tunnel cooling system.
Description
Technical field
The design field of high velocity air temperature measuring equipment under low temperature environment is the utility model is related to, specifically one kind is used for
The stagnation temperature framed bent of continuous high-speed wind-tunnel hydrojet nitrogen cooling system.
Background technology
Reynolds number is the important similar parameter of wind tunnel experiment simulated flight device practical flying ability, develops high Reynola number wind tunnel
Development to China's Aviation Industry and science and techniques of defence has its own strategic significance and engineering application value.Reynolds number is close by fluid
Degree, temperature, speed and moulded dimension determine that in the case of experimental section size with fluid media (medium) not malleable, cooling can increase
Fluid density, reduce viscosity, be that a kind of improve tests Reynolds number effective way.Liquid nitrogen is a kind of lower boiling inert material
Matter, have the characteristics that evaporation is fast, chemical property is stable, the gasification of liquid nitrogen can be utilized by way of spraying liquid nitrogen into wind-tunnel
Endothermic effect, the heat in wind-tunnel is taken away, so as to realize reduction gas flow temperature, the purpose of increase experiment Reynolds number.China is current
Still belong to blank in terms of low temperature continuous high-speed wind-tunnel, therefore, develop the liquid nitrogen cooling system suitable for continuous high-speed wind-tunnel
China's Wind Tunnel Technique is innovated significant with weapons SoS.
The final purpose of continuous high-speed wind-tunnel hydrojet nitrogen cooling system is exactly to reduce the temperature of wind-tunnel interior air-flow, therefore,
How accurately to measure total airflow temperature under the operating mode of wind-tunnel cooling operation is one of its key technology that must be solved.According to continuous
Physical characteristic of the design feature and air-flow of formula high-speed wind tunnel under high speed, supercharging and low-temperature condition, total temperature measurement device are set
Meter need to do special consideration in the following aspects：1) wind turbine apparatus narrow space, but the requirement of wind tunnel experiment stream field quality
It is very high, and because continuous wind tunnel is full-closed structure, therefore conventional non-contact temperature measuring is difficult to, and therefore, the thermometric of use
Device needs to be installed on wind turbine apparatus progress contact type measurement, and it has the streamlined aerodynamic configuration of low windage, so as to ensure
The flow field of wind-tunnel is not destroyed.2) air velocity in wind-tunnel is high, and liquid nitrogen vaporization heat absorption is fast, and temperature diffusion time is limited, single-point
Measurement is difficult to the uniform distribution for understanding temperature, therefore must carry out multimetering, to obtain the global temperature of wind-tunnel flow field
Distribution.3) expansion due to liquid nitrogen and evaporation endothermic characteristic, wind-tunnel have the characteristics of pressure is high, temperature is low when cooling and running,
Therefore measurement apparatus need to select low temperature resistant and high voltage bearing material, to ensure the safety of measuring apparatus and construction of wind tunnel.4) it is continuous
Formula high-speed wind tunnel is compact-sized, is not easily decomposed, therefore used temperature measuring equipment need are simple in construction, are easily installed, dismantle.
As the above analysis, the structure of continuous low-temperature wind-tunnel is special, operating condition is complicated, it is necessary to develop a set of be used for
Total temperature measurement device of continuous high-speed wind-tunnel hydrojet nitrogen cooling system, with accurate on the premise of Flow Field in Wind Tunnel quality is not influenceed
Obtain the Temperature Distribution of wind-tunnel interior air-flow.
The content of the invention
The defects of in order to overcome existing thermometry to be used in continuous low-temperature wind-tunnel, solve contact type measurement and flow field
Contradiction between interference, low temperature resistant total temperature measurement device of streamlined aerodynamic configuration of the design with low windage, realizes low temperature ring
The multiple spot of border downstream temperature accurately measures, and the utility model proposes one kind to be applied to continuous high-speed wind-tunnel spray liquid nitrogen cooling system
The stagnation temperature framed bent of system.
The technical solution of the utility model is：
A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system, it is characterised in that：Including more
Individual temp probe, multiple probe pole, framed bent, base, end plate and data conductors；Temp probe is identical with probe pole number；
The temp probe uses semiellipsoid profile, is installed on using threaded connection on probe pole, temp probe
Data conductor is drawn by the central through hole of pop one's head in pole central through hole and framed bent；
The probe pole is provided with axial central through hole；Probe pole front end installation temp probe, rear end is consolidated with framed bent
Fixed connection；Multiple probe poles are along framed bent short transverse equidistantly distributed；
The framed bent is provided with for the central through hole by data conductor along short transverse；Framed bent is along the transversal of short transverse
Face uses along tunnel airstream direction thick middle, front and rear narrow cross sectional shape, probe pole and is arranged on framed bent front end；
The base upper end is fixedly connected with framed bent bottom, and lower end is fixedly installed in hole wall under wind-tunnel；
The endplate root is fixedly connected at the top of framed bent, and hole wall on wind-tunnel is fixedly installed at the top of end plate.
Further preferred scheme, a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system,
It is characterized in that：The temp probe base diameter is d, length 1.5d；From thermocouple temperature sensitive element, range is -200 DEG C
~500 DEG C, precision is ± 0.1 DEG C.
Further preferred scheme, a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system,
It is characterized in that：Pole external diameter of popping one's head in is 1.2d, internal diameter d, length 28d.
Further preferred scheme, a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system,
It is characterized in that：The a diameter of 6d of framed bent central through hole；Cross section of the framed bent along short transverse is used along among tunnel airstream direction
Thick, front and rear 8 narrow side shape shapes, framed bent nose thickness are 2d, and center section thickness is 10d, rear end thickness contraction to 6d.
Further preferred scheme, a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system,
It is characterized in that：Base lower end is embedded in hole wall under wind-tunnel；It is long 50d at the top of end plate, wide 40d, thick 6d rectangular flat plate, leads to
Cross and be threadedly connected to hole wall on wind-tunnel.
Further preferred scheme, a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system,
It is characterized in that：Data conductor is using the silver-plated anti-interference data wire of establishment.
Beneficial effect
The utility model overcomes the defects of existing thermometry uses in continuous low-temperature wind-tunnel, passes through stagnation temperature framed bent
Low windage streamlined Design of Aerodynamic Configuration, solve the problems, such as measurement apparatus to Flow Field in Wind Tunnel disturb；Using temp probe
Longitudinal arrangement formula is arranged, is realized multipoint mode flow field stagnation temperature and is accurately measured；The utility model proposes stagnation temperature bent structure it is simple,
Dismounting is easily installed, suitable for the working environment of cryogenic high pressure.Using the technical program, wind-tunnel cooling system stagnation temperature is realized
Accurate measurement, technical support is provided to build up China's first set continuous high-speed wind-tunnel cooling system.
Additional aspect and advantage of the present utility model will be set forth in part in the description, partly by from following description
In become obvious, or by it is of the present utility model practice recognize.
Brief description of the drawings
Of the present utility model above-mentioned and/or additional aspect and advantage will in the description from combination accompanying drawings below to embodiment
Become obvious and be readily appreciated that, wherein：
Accompanying drawing 1 is stagnation temperature bent structure figure；
1- temp probes, 2- probe poles, 3- framed bents, 4- bases, 5- end plates, 6- data conductors.
Accompanying drawing 2 is stagnation temperature framed bent partial enlarged drawing；
1- temp probes, 2- probe poles, 3- framed bents.
Accompanying drawing 3 is stagnation temperature framed bent and NF-6 wind-tunnel installation diagrams；
1- temp probes, 2- probe poles, 3- framed bents, hole wall under 7- wind-tunnel stable sections, hole wall on 8- wind-tunnel stable sections, 6-
Data conductor.
Accompanying drawing 4 is stagnation temperature framed bent molding surface size and local Fang great Tu；
1- temp probes, 2- probe poles, 3- framed bents.
Accompanying drawing 5 is the change of normal pressure pull-down test stagnation temperature；
Accompanying drawing 6 is the change of normal pressure pull-down test Ma numbers；
Accompanying drawing 7 is the change of normal pressure pull-down test stagnation pressure；
Accompanying drawing 8 is pressure charging temperature reduction experiment stagnation temperature change；
Accompanying drawing 9 is pressure charging temperature reduction experiment Ma number changes；
Accompanying drawing 10 is the change of replica test stagnation pressure.
Embodiment
Embodiment of the present utility model is described below in detail, the example of the embodiment is shown in the drawings, wherein from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Below by ginseng
The embodiment for examining accompanying drawing description is exemplary, it is intended to for explaining the utility model, and it is not intended that to the utility model
Limitation.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", " length ", " width
Degree ", " thickness ", " on ", " under ", "front", "rear", "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer ",
The orientation or position relationship of the instructions such as " clockwise ", " counterclockwise " be based on orientation shown in the drawings or position relationship, be only for
Be easy to describe the utility model and simplify to describe, rather than instruction or imply signified device or element must have it is specific
Orientation, with specific azimuth configuration and operation, therefore it is not intended that to limitation of the present utility model.
The present embodiment is a kind of stagnation temperature framed bent of continuous high-speed wind-tunnel hydrojet nitrogen cooling system, including 9 temp probes,
9 probe poles, framed bent, base, end plate and data conductor, for continuous high-speed wind-tunnel liquid nitrogen cooling system airflow stagnation temperature
Multimetering.As shown in Figure 1 and Figure 2.
The temp probe of the present embodiment selects thermocouple temperature sensitive element, for gathering the gas flow temperature in wind-tunnel, range for-
200 DEG C~500 DEG C, precision is ± 0.1 DEG C.Temp probe is into semiellipsoid profile, base diameter 5mm, length 7.5mm,
See Fig. 4.Temp probe totally 9, gauge size is identical, is installed on probe pole using threaded connection, probe data wire passes through
Pole is drawn with framed bent inner chamber, sees Fig. 4.
The probe pole of the present embodiment is made up of stainless steel material, and manhole, external diameter 6mm are left in centre, and internal diameter is
5mm, length 140mm, is shown in Fig. 4.Probe pole totally 9, gauge size is identical, probe pole front end installation temp probe, after
End welding and framed bent.9 probe poles spacing 300mm, see Fig. 4 along framed bent short transverse equidistantly distributed.
The framed bent of the present embodiment is made up of stainless steel material, and centre is left for the manhole by data conductor, leads to
Bore dia is 30mm, the total a height of 3000mm of framed bent.In order to ensure the streamlined aerodynamic configuration of low windage of framed bent windward side, framed bent horizontal stroke
Section is the small 8 side shapes broad in the middle in two.Framed bent nose thickness is 10mm, for installing pole of popping one's head in；Center section thickness is
50mm, for opened hole cabling；Rear end thickness contraction is to 30mm, the air-flow separation with reduction around its flowing, reduction profile drag,
See Fig. 3, Fig. 4.
The base of the present embodiment is made up of stainless steel material, for connecting hole wall under framed bent and wind-tunnel.Base cross section with
Framed bent is identical, and upper end is connected through a screw thread framed bent bottom, and lower end is embedded in hole wall under wind-tunnel, to reach fixed and positioning framed bent
Purpose.
The end plate of the present embodiment is made up of stainless steel material, for connecting hole wall on framed bent and wind-tunnel.Endplate root is transversal
Face is identical with framed bent, is connected through a screw thread at the top of framed bent, and end plate top is long 250mm, wide 200mm, thick 30mm rectangle are put down
Plate, hole wall on wind-tunnel is threadingly attached to, to reach fixed and positioning framed bent purpose.
The data conductor of the present embodiment totally 9, passes through pole and the row of popping one's head in from the silver-plated anti-interference dedicated data line of establishment
Frame inner chamber is drawn, and for connecting temp probe and data acquisition instrument, realizes the high-fidelity transfer of tunnel airstream temperature parameter.
In the present embodiment, stagnation temperature framed bent is installed vertically on wind-tunnel stable section central symmetry plane by base and end plate,
Its center base lower end is embedded in hole wall under wind-tunnel stable section, and end plate is threadingly attached to hole wall on wind-tunnel, and temp probe is parallel
In direction of flow, data conductor is drawn by hole wall on pole of popping one's head in, framed bent inner chamber and wind-tunnel stable section, and is connected to data and is adopted
Collect instrument.The assembly relation of stagnation temperature framed bent and wind-tunnel is as shown in Figure 3.After the installation for completing stagnation temperature framed bent, start wind-tunnel, operation spray
Liquid nitrogen cooling system, model experiment operating mode is chosen, test the service behaviour of stagnation temperature framed bent under normal pressure and pressurized environment respectively.
Atmospheric pressure environment testing results：
By taking M=0.5 normal pressure pull-down test as an example, Fig. 5 gives the situation of change of its stable section stagnation temperature, and Fig. 6 gives
The situation of change of its stable section test section Ma number, Fig. 7 give the situation of change of its stable section stagnation pressure.As can be known from Figure：
1) average value of 9 stagnation temperature measuring points of stable section reaches -20 DEG C, and meets
2) average value of test section Ma numbers reaches 0.5, and Mach number deviation is | Δ Ma |≤0.003, that is, and meet σMa≤
0.003；
3) average value of stable section stagnation pressure is 1.022bar, and its amplitude of variation meets
Pressurized environment testing results：
By taking M=0.8 pressure charging temperature reduction experiment as an example, Fig. 8 gives the situation of change of its stable section stagnation temperature, and Fig. 9 gives
The situation of change of its stable section test section Ma number, Figure 10 give the situation of change of its stable section stagnation pressure.As can be known from Figure：
1) average value of 9 stagnation temperature measuring points of stable section reaches -20 DEG C, and meets
2) average value of test section Ma numbers reaches 0.8, and Mach number deviation is | Δ Ma |≤0.003, that is, and meet σMa≤
0.003；
3) average value of stable section stagnation pressure reaches 1.7bar, and its amplitude of variation meets
By above-mentioned testing results and repeated experiment result, the stagnation temperature framed bent of the utility model design is in low temperature ring
Working stability, dependable performance under border, realize the multimetering in cryonetic wind tunnel temperature field；Wind-tunnel Mach number, stagnation pressure control is stable,
Accurately, show that the framed bent configuration design of this stagnation temperature is reasonable, Flow Field in Wind Tunnel is not interfered；The selection of stagnation temperature framed bent is suitable, installs just
Victory, it is applicable to the complex working conditions such as low temperature, high pressure.
Although embodiment of the present utility model has been shown and described above, it is to be understood that above-described embodiment is
Exemplary, it is impossible to it is interpreted as not departing from the utility model to limitation of the present utility model, one of ordinary skill in the art
Principle and objective in the case of above-described embodiment can be changed in the scope of the utility model, change, replace and
Modification.
Claims (6)
- A kind of 1. stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system, it is characterised in that：Including multiple temperature Probe, multiple probe pole, framed bent, base, end plate and data conductors；Temp probe is identical with probe pole number；The temp probe uses semiellipsoid profile, is installed on using threaded connection on probe pole, the data of temp probe Wire is drawn by the central through hole of pop one's head in pole central through hole and framed bent；The probe pole is provided with axial central through hole；Probe pole front end installation temp probe, rear end is fixed with framed bent to be connected Connect；Multiple probe poles are along framed bent short transverse equidistantly distributed；The framed bent is provided with for the central through hole by data conductor along short transverse；Framed bent is adopted along the cross section of short transverse Framed bent front end is arranged on along tunnel airstream direction thick middle, front and rear narrow cross sectional shape, probe pole；The base upper end is fixedly connected with framed bent bottom, and lower end is fixedly installed in hole wall under wind-tunnel；The endplate root is fixedly connected at the top of framed bent, and hole wall on wind-tunnel is fixedly installed at the top of end plate.
- 2. a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system according to claim 1, its feature It is：The temp probe base diameter is d, length 1.5d；From thermocouple temperature sensitive element, range is -200 DEG C~500 DEG C, precision is ± 0.1 DEG C.
- 3. a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system according to claim 2, its feature It is：Pole external diameter of popping one's head in is 1.2d, internal diameter d, length 28d.
- 4. a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system according to claim 2, its feature It is：The a diameter of 6d of framed bent central through hole；Cross section of the framed bent along short transverse is used along tunnel airstream direction thick middle, front and rear 8 narrow side shape shapes, framed bent nose thickness are 2d, and center section thickness is 10d, rear end thickness contraction to 6d.
- 5. a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system according to claim 2, its feature It is：Base lower end is embedded in hole wall under wind-tunnel；It is long 50d at the top of end plate, wide 40d, thick 6d rectangular flat plate, passes through screw thread It is connected to hole wall on wind-tunnel.
- 6. a kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system according to claim 2, its feature It is：Data conductor is using the silver-plated anti-interference data wire of establishment.
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| CN201720556502.1U CN206740354U (en) | 2017-05-18 | 2017-05-18 | A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201720556502.1U CN206740354U (en) | 2017-05-18 | 2017-05-18 | A kind of stagnation temperature framed bent for continuous high-speed wind-tunnel hydrojet nitrogen cooling system |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367827A (en) * | 2018-11-20 | 2019-02-22 | 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 Multi probe water-cooled test framed bent |
| CN111855135A (en) * | 2020-07-30 | 2020-10-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel airflow average speed measuring bent frame and measuring method |
| CN112556971A (en) * | 2020-12-21 | 2021-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring length of interference zone of transonic wind tunnel support system |
| CN114136647A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Supersonic speed high-temperature three-dimensional flow field measuring device |
-
2017
- 2017-05-18 CN CN201720556502.1U patent/CN206740354U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109367827A (en) * | 2018-11-20 | 2019-02-22 | 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 Multi probe water-cooled test framed bent |
| CN109367827B (en) * | 2018-11-20 | 2023-08-22 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-probe water-cooled test bent |
| CN111855135A (en) * | 2020-07-30 | 2020-10-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel airflow average speed measuring bent frame and measuring method |
| CN111855135B (en) * | 2020-07-30 | 2022-07-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | Wind tunnel airflow average speed measuring bent frame and measuring method |
| CN112556971A (en) * | 2020-12-21 | 2021-03-26 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for measuring length of interference zone of transonic wind tunnel support system |
| CN114136647A (en) * | 2021-10-20 | 2022-03-04 | 中国航发四川燃气涡轮研究院 | Supersonic speed high-temperature three-dimensional flow field measuring device |
| CN114136647B (en) * | 2021-10-20 | 2023-10-03 | 中国航发四川燃气涡轮研究院 | Supersonic high-temperature three-dimensional flow field measuring device |
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| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20171212 |