CN109765031A - A kind of balance strut for wind-tunnel hot exhaust interference test - Google Patents
A kind of balance strut for wind-tunnel hot exhaust interference test Download PDFInfo
- Publication number
- CN109765031A CN109765031A CN201910183433.8A CN201910183433A CN109765031A CN 109765031 A CN109765031 A CN 109765031A CN 201910183433 A CN201910183433 A CN 201910183433A CN 109765031 A CN109765031 A CN 109765031A
- Authority
- CN
- China
- Prior art keywords
- test
- nozzle
- strut
- main body
- wind
- 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
- 238000012360 testing method Methods 0.000 title claims abstract description 70
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims abstract description 41
- 238000001816 cooling Methods 0.000 claims abstract description 9
- 239000000498 cooling water Substances 0.000 claims description 9
- 238000005259 measurement Methods 0.000 claims description 6
- 229910001369 Brass Inorganic materials 0.000 claims description 3
- 239000010951 brass Substances 0.000 claims description 3
- 239000000463 material Substances 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 239000000523 sample Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 abstract description 5
- 239000007789 gas Substances 0.000 abstract 6
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 abstract 2
- 229910052757 nitrogen Inorganic materials 0.000 abstract 1
- TXEYQDLBPFQVAA-UHFFFAOYSA-N tetrafluoromethane Chemical compound FC(F)(F)F TXEYQDLBPFQVAA-UHFFFAOYSA-N 0.000 abstract 1
- 238000000034 method Methods 0.000 description 2
- 238000011160 research Methods 0.000 description 2
- 239000007921 spray Substances 0.000 description 2
- 206010044565 Tremor Diseases 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000011161 development Methods 0.000 description 1
- 230000006872 improvement Effects 0.000 description 1
- 238000001727 in vivo Methods 0.000 description 1
- 230000003993 interaction Effects 0.000 description 1
- 230000004044 response Effects 0.000 description 1
- 238000004088 simulation Methods 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
Landscapes
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention discloses a kind of balance strut for wind-tunnel hot exhaust interference test, which includes strut main body, gas path module, water cooling module, debugging nozzle and test nozzle.Strut main body is used for jet flow air inlet for installing balance and model, gas path module, and water cooling module is for cooling down strut, to reduce the influence that the high temperature of spout gas measures balance.Jet flow air inlet uses the mixed gas of carbon tetrafluoride and nitrogen, by changing the proportion of two kinds of gas to adjust the specific heat ratio of mixed gas.The preceding only installation and debugging nozzle of test, debugs the total temperature stagnation pressure of jet flow;Debugging nozzle is removed when test, installs test nozzle and model, carries out wind tunnel test according to the state of debugging.Balance strut for wind-tunnel hot exhaust interference test of the invention is suitable for the wind-tunnel thermal jet test under rarefied atmosphere environment, can measure influence of the Jet enterference to model aerodynamic force.
Description
Technical field
The invention belongs to wind-tunnel technique fields, and in particular to a kind of balance branch for wind-tunnel hot exhaust interference test
Bar.
Background technique
With the development of aeronautical and space technology, the flight Mach number of aircraft is also being continuously improved, this control to aircraft
System proposes stern challenge.There are the control of traditional, pneumatic rudder face and jet control with relatively broad at present.
Jet control technology is to utilize to be mounted on jet flow reaction force caused by carry-on miniature jet engine
To the new control system that aircraft is directly controlled, compared with traditional rudder face control, jet control is suitable for All Speed Range
With full airspace, have many advantages, such as that response is fast, high-efficient;But the interference caused by jet flow, incoming flow interaction is a kind of typical case
Complex Phenomena in Vertical Bell Jar, current research is deep not enough.
In practical study, lateral jet is simulated in Chang Liyong wind tunnel test.Jet enterference wind tunnel test at present is ground
Study carefully based on the test of cold Jet enterference, hot exhaust interference test research is less, the main reason is that existing solid charge rocket
The true jet engine of simulation of engine leads to problems such as jet flow shakiness in chamber pressure, low efficiency, efficiency test time short.With
The continuous improvement of extensive application and jet control required precision of the jet control technology in aircraft, hot exhaust interfere wind-tunnel examination
Testing demand also constantly enhances, more urgent especially for the hot exhaust the Study of Interference under rarefied atmosphere environment.In order to accurately survey
Measure model aerodynamic force suffered under hot exhaust interference effect, need to design it is a kind of be assembled and used with wind-tunnel balance suitable for dilute
The strut of wind-tunnel hot exhaust interference test under thin atmospheric environment.
Summary of the invention
Technical problem to be solved by the invention is to provide a kind of balance struts for wind-tunnel hot exhaust interference test.
Balance strut for wind-tunnel hot exhaust interference test of the invention, its main feature is that being suitable under rarefied atmosphere environment
Wind-tunnel hot exhaust interference test, the balance strut include strut main body, gas path module, water cooling module, debugging nozzle and examination
Test nozzle;
The strut main body is cylinder, and the front end of strut main body is connected with balance by collet, the rear end of strut main body
It is equipped by the tulwar of the conical surface and wind-tunnel attack angle mechanism;
The gas path module includes the air inlet of airflow line and airflow line, airflow line be fixed in strut main body and with
Strut main body is coaxial, and air inlet is located in strut main body to be connected to external gas source, and there is an inner cavity in the end of airflow line, interior
Chamber is opened in strut main body there are two threaded hole, and nozzle, another threaded hole joint test nozzle are debugged in a threaded hole connection;
The water cooling module includes water pipe, water circulation hole and cooling water cover, and water pipe is two and parallel is fixed on strut master
In vivo and the water pipe coaxial with strut main body, cooling water enter from a water pipe, flow through the water positioned at the intracorporal cavity of strut master
It is flowed out after flowing circulation port through another water pipe, cooling water cover, which is covered, seals water flow circuits on water circulation hole;
Pressure tap is provided on the debugging nozzle, the stagnation pressure of installation total-pressure probe measurement hot exhaust, debugging spray on pressure tap
It is also provided with thermometer hole on mouth, the total temperature of thermocouple measurement hot exhaust is installed on thermometer hole;
The model cover board and test model is equipped, and test nozzle outlet is provided on model cover board, and test nozzle is sprayed from test
Mouth outlet is stretched out, and test nozzle is concordant with model lid surface, is had the gap between test nozzle and test nozzle outlet.
The relationship of the diameter D of the diameter d and strut main body of the airflow line is d=1/4D, and the material of airflow line is
Brass.
The water circulation hole replaces with spiral shape circulating line.
Balance strut for wind-tunnel hot exhaust interference test of the invention is suitable for the wind-tunnel heat under rarefied atmosphere environment
Spray test, can measure influence of the Jet enterference to model aerodynamic force.
Detailed description of the invention
Fig. 1 is the three-dimensional axonometric drawing of the balance strut for wind-tunnel hot exhaust interference test of the invention;
Fig. 2 is the bottom view of the balance strut for wind-tunnel hot exhaust interference test of the invention;
Fig. 3 is the debugging nozzle three-dimensional axonometric drawing in the balance strut for wind-tunnel hot exhaust interference test of the invention;
Fig. 4 is the debugging nozzle cross-sectional view in the balance strut for wind-tunnel hot exhaust interference test of the invention;
Fig. 5 is the test nozzle three-dimensional axonometric drawing in the balance strut for wind-tunnel hot exhaust interference test of the invention;
Fig. 6 is the test nozzle cross-sectional view in the balance strut for wind-tunnel hot exhaust interference test of the invention;
Fig. 7 is the model scheme of installation of the balance strut for wind-tunnel hot exhaust interference test of the invention;
In figure, 1. conical surface, 2. air inlet, 3. airflow line, 4. thermometer hole, 5. water cover 6. debugs the test of 7. pressure tap 8. of nozzle
9. water pipe of nozzle, 10. water circulation hole, 11. test nozzle exports 12. model cover boards.
Specific embodiment
The present invention will be described in detail with reference to the accompanying drawings and examples.
As shown in Fig. 1 ~ 6, the balance strut for wind-tunnel hot exhaust interference test of the invention includes strut main body, gas circuit
Module, water cooling module, debugging nozzle 6 and test nozzle 8;
The strut main body is cylinder, and the front end of strut main body is connected with balance by collet, the rear end of strut main body
It is equipped by the tulwar of the conical surface 1 and wind-tunnel attack angle mechanism;
The gas path module includes the air inlet 2 of airflow line 3 and airflow line 3, and airflow line 3 is fixed in strut main body
And it is coaxial with strut main body, air inlet 2 is located at outside strut main body to be connected to external gas source, and the end of airflow line 3 has one
Inner cavity, inner cavity are opened in strut main body there are two threaded hole, a threaded hole connection debugging nozzle 6, another threaded hole connects
Test nozzle 8;
The water cooling module includes water pipe 9, water circulation hole 10 and cooling water cover 5, and water pipe 9 is two and parallel is fixed on branch
In bar main body and the water pipe coaxial with strut main body, cooling water enter from a water pipe, flow through positioned at the intracorporal cavity of strut master
Water circulation hole 10 after flowed out through another water pipe, cooling water cover 5, which is covered, seals water flow circuits on water circulation hole 10;
Pressure tap 7 is provided on the debugging nozzle 6, the stagnation pressure of installation total-pressure probe measurement hot exhaust, debugging on pressure tap 7
It is also provided with thermometer hole 4 on nozzle 6, the total temperature of thermocouple measurement hot exhaust is installed on thermometer hole 4.
Embodiment 1
The course of work of the present embodiment is as follows:
1. installation and debugging nozzle 6 measures total temperature stagnation pressure, obtain testing required operating status, removes debugging nozzle 6, and block;
2. installing test nozzle 8, as shown in fig. 7, installing model in wind-tunnel, the front end of strut main body is passed through into wedge key and pin key
It is mounted on the rear end of balance, model in wind tunnel is installed by collet in the front end of balance, and the rear end of model in wind tunnel is covered
It covers on test nozzle 8, there is a model cover board 12 on the surface of model in wind tunnel corresponding with test nozzle 8, on model cover board 12
It is provided with test nozzle outlet 11, test nozzle 8 is stretched out from test nozzle outlet 11, and test nozzle 8 and 12 surface of model cover board are flat
Together, it is had the gap between test nozzle 8 and test nozzle outlet 11.The pass of the diameter D of the diameter d and strut main body of airflow line 3
System is d=1/4D, and the material of airflow line 5 is brass.
3. when test, after Flow Field in Wind Tunnel foundation, spout gas is flowed into from air inlet 2, flow through in airflow line 3 reaches
Chamber is finally sprayed from test nozzle 8, to measure influence of the Jet enterference to model aerodynamic force.
Water circulation hole in the present embodiment can be replaced spiral shape circulating line.
Claims (3)
1. a kind of balance strut for wind-tunnel hot exhaust interference test, which is characterized in that the balance strut includes strut
Main body, gas path module, water cooling module, debugging nozzle (6) and test nozzle (8);
The strut main body is cylinder, and the front end of strut main body is connected with balance by collet, the rear end of strut main body
It is equipped by the tulwar of the conical surface (1) and wind-tunnel attack angle mechanism;
The gas path module includes the air inlet (2) of airflow line (3) and airflow line (3), and airflow line (3) is fixed on branch
In bar main body and coaxial with strut main body, air inlet (2) is located in strut main body to be connected to external gas source, airflow line (3)
End have an inner cavity, inner cavity opens that there are two threaded holes, threaded hole connection debugging nozzle (6) in strut main body, separately
One threaded hole joint test nozzle (8);
The water cooling module includes water pipe (9), water circulation hole (10) and cooling water cover (5), and water pipe (9) is two parallel
It is fixed in strut main body and the water pipe coaxial with strut main body, cooling water enters from a water pipe, flow through positioned at strut main body
The water circulation hole (10) of interior cavity is flowed out by another water pipe, and cooling water cover (5) are covered close on water circulation hole (10)
Seal water flow circuits;
It is provided with pressure tap (7) on the debugging nozzle (6), the total of total-pressure probe measurement hot exhaust is installed on pressure tap (7)
Pressure is debugged and is also provided with thermometer hole (4) on nozzle (6), and the total temperature of thermocouple measurement hot exhaust is installed on thermometer hole (4);
The model cover board (12) and test model is equipped, and test nozzle outlet (11), test are provided on model cover board (12)
Nozzle (8) is stretched out from test nozzle outlet (11), test nozzle (8) and model cover board (12) flush, test nozzle (8) with
It is had the gap between test nozzle outlet (11).
2. the balance strut according to claim 1 for wind-tunnel hot exhaust interference test, which is characterized in that the gas
The relationship of the diameter D of the diameter d and strut main body in flow tube road (3) is d=1/4D, and the material of airflow line (3) is brass.
3. the balance strut according to claim 1 for wind-tunnel hot exhaust interference test, which is characterized in that the water
Stream circulation port (10) replaces with spiral shape circulating line.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201910183433.8A CN109765031A (en) | 2019-03-12 | 2019-03-12 | A kind of balance strut for wind-tunnel hot exhaust interference test |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
CN201910183433.8A CN109765031A (en) | 2019-03-12 | 2019-03-12 | A kind of balance strut for wind-tunnel hot exhaust interference test |
Publications (1)
Publication Number | Publication Date |
---|---|
CN109765031A true CN109765031A (en) | 2019-05-17 |
Family
ID=66458684
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
CN201910183433.8A Pending CN109765031A (en) | 2019-03-12 | 2019-03-12 | A kind of balance strut for wind-tunnel hot exhaust interference test |
Country Status (1)
Country | Link |
---|---|
CN (1) | CN109765031A (en) |
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110595722A (en) * | 2019-11-01 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Heat-preservation flexible hose for hypersonic wind tunnel heat jet flow interference test |
CN113267312A (en) * | 2021-07-19 | 2021-08-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test model for high-temperature wind tunnel |
CN113267320A (en) * | 2021-07-19 | 2021-08-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water cooling device for rod type balance of high-temperature wind tunnel |
CN113280995A (en) * | 2021-07-19 | 2021-08-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Cooling device for high-temperature wind tunnel model |
CN113340558A (en) * | 2021-08-05 | 2021-09-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Rod type balance protection device applied to multistage hypersonic wind tunnel test model |
CN113358320A (en) * | 2021-08-10 | 2021-09-07 | 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 force of interference of jet flow of upstream air for high-speed wind tunnel |
CN113588200A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-flow reverse jet test device and method for hypersonic aircraft |
CN113588202A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-body thermal separation test simulation device and test method for high-altitude high-speed thin environment |
CN113588201A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
CN113740023A (en) * | 2021-08-31 | 2021-12-03 | 中国航天空气动力技术研究院 | Novel jet flow supporting rod |
CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
CN113607375B (en) * | 2021-06-26 | 2023-11-17 | 成都凯迪精工科技有限责任公司 | Wind tunnel model balance heat insulation system |
Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2002340733A (en) * | 2001-05-11 | 2002-11-27 | National Aerospace Laboratory Of Japan | Free jet hypersonic wind tunnel testing apparatus |
CN105973565A (en) * | 2016-06-29 | 2016-09-28 | 中国航天空气动力技术研究院 | Lateral jet flow system for wind tunnel interference test |
CN107860554A (en) * | 2017-12-06 | 2018-03-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment and test method in wind tunnel test |
CN108088649A (en) * | 2018-01-22 | 2018-05-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | The model equipment and test method that jet pipe is connected with shape in wind tunnel test |
CN108692909A (en) * | 2018-06-27 | 2018-10-23 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of water-cooling structure being thermally shielded protection to wind-tunnel balance |
CN209606052U (en) * | 2019-03-12 | 2019-11-08 | 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 balance strut for wind-tunnel hot exhaust interference test |
-
2019
- 2019-03-12 CN CN201910183433.8A patent/CN109765031A/en active Pending
Patent Citations (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
JP2002340733A (en) * | 2001-05-11 | 2002-11-27 | National Aerospace Laboratory Of Japan | Free jet hypersonic wind tunnel testing apparatus |
CN105973565A (en) * | 2016-06-29 | 2016-09-28 | 中国航天空气动力技术研究院 | Lateral jet flow system for wind tunnel interference test |
CN107860554A (en) * | 2017-12-06 | 2018-03-30 | 中国空气动力研究与发展中心超高速空气动力研究所 | Tail jet Test Integrated model equipment and test method in wind tunnel test |
CN108088649A (en) * | 2018-01-22 | 2018-05-29 | 中国空气动力研究与发展中心超高速空气动力研究所 | The model equipment and test method that jet pipe is connected with shape in wind tunnel test |
CN108692909A (en) * | 2018-06-27 | 2018-10-23 | 中国空气动力研究与发展中心高速空气动力研究所 | A kind of water-cooling structure being thermally shielded protection to wind-tunnel balance |
CN209606052U (en) * | 2019-03-12 | 2019-11-08 | 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 balance strut for wind-tunnel hot exhaust interference test |
Non-Patent Citations (1)
Title |
---|
唐志共 等: "横向喷流干扰/控制研究进展", 实验流体力学, vol. 24, no. 4, pages 1 - 6 * |
Cited By (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
CN110595722A (en) * | 2019-11-01 | 2019-12-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Heat-preservation flexible hose for hypersonic wind tunnel heat jet flow interference test |
CN113607375B (en) * | 2021-06-26 | 2023-11-17 | 成都凯迪精工科技有限责任公司 | Wind tunnel model balance heat insulation system |
CN113267312B (en) * | 2021-07-19 | 2021-09-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test model for high-temperature wind tunnel |
CN113280995A (en) * | 2021-07-19 | 2021-08-20 | 中国空气动力研究与发展中心超高速空气动力研究所 | Cooling device for high-temperature wind tunnel model |
CN113280995B (en) * | 2021-07-19 | 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 | Cooling device for high-temperature wind tunnel model |
CN113267320B (en) * | 2021-07-19 | 2021-09-28 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water cooling device for rod type balance of high-temperature wind tunnel |
CN113267320A (en) * | 2021-07-19 | 2021-08-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Water cooling device for rod type balance of high-temperature wind tunnel |
CN113267312A (en) * | 2021-07-19 | 2021-08-17 | 中国空气动力研究与发展中心超高速空气动力研究所 | Test model for high-temperature wind tunnel |
CN113340558A (en) * | 2021-08-05 | 2021-09-03 | 中国空气动力研究与发展中心高速空气动力研究所 | Rod type balance protection device applied to multistage hypersonic wind tunnel test model |
CN113340558B (en) * | 2021-08-05 | 2021-10-29 | 中国空气动力研究与发展中心高速空气动力研究所 | Rod type balance protection device applied to multistage hypersonic wind tunnel test model |
CN113358320A (en) * | 2021-08-10 | 2021-09-07 | 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 force of interference of jet flow of upstream air for high-speed wind tunnel |
CN113740023B (en) * | 2021-08-31 | 2024-02-09 | 中国航天空气动力技术研究院 | Novel jet flow supporting rod |
CN113740023A (en) * | 2021-08-31 | 2021-12-03 | 中国航天空气动力技术研究院 | Novel jet flow supporting rod |
CN113588202A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-body thermal separation test simulation device and test method for high-altitude high-speed thin environment |
CN113588202B (en) * | 2021-09-30 | 2021-12-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-body thermal separation test simulation device and test method for high-altitude high-speed thin environment |
CN113899516A (en) * | 2021-09-30 | 2022-01-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | Ground simulation device and method for rocket engine jet flow interference effect |
CN113588200B (en) * | 2021-09-30 | 2021-12-07 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-flow reverse jet test device and method for hypersonic aircraft |
CN113588201B (en) * | 2021-09-30 | 2022-04-12 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
CN113588201A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | Thermal jet flow interference test device and test method for high-altitude high-speed thin environment |
CN113588200A (en) * | 2021-09-30 | 2021-11-02 | 中国空气动力研究与发展中心超高速空气动力研究所 | High-flow reverse jet test device and method for hypersonic aircraft |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
CN109765031A (en) | A kind of balance strut for wind-tunnel hot exhaust interference test | |
CN106840591B (en) | A kind of experimental rig directly measuring jet flow thrust | |
CN109250149A (en) | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation | |
CN109506744B (en) | Air flow calibration method for venturi nozzle of aircraft engine complete machine test | |
CN109765030A (en) | A kind of wind-tunnel hot exhaust interference test device | |
CN105424369B (en) | A kind of aero-engine aerodynamic model exerciser | |
CN109470401B (en) | Straight-rod airspeed tube with attack angle resolving function | |
CN107655652B (en) | Air supply device and air supply method for small-thrust jet nozzle in wind tunnel test | |
CN113588200B (en) | High-flow reverse jet test device and method for hypersonic aircraft | |
CN111537181B (en) | Thermal noise wind tunnel based on arc heating and test method | |
CN110595729A (en) | Multi-jet flow interference test device for hypersonic wind tunnel surface symmetry model | |
CN114235321B (en) | Wind tunnel force measurement experimental device integrating gas rudder and spray pipe | |
CN209606052U (en) | A kind of balance strut for wind-tunnel hot exhaust interference test | |
CN106092495A (en) | The measuring method of aircraft body resistance in wind tunnel test | |
CN111792061A (en) | Pneumatic thermal test device and method utilizing shock wave boundary layer interference | |
CN105181317A (en) | Rudderpost heat sealing test device | |
CN211740626U (en) | Combined power multichannel spray pipe test device | |
CN103499447A (en) | Zero mach number testing device applied to turbine engine | |
CN208947639U (en) | Flow tunnel testing device for air suction type hypersonic vehicle radome fairing separation simulation | |
CN204944736U (en) | A kind of total pressure measurement probe | |
CN112577703A (en) | Arc wind tunnel variable angle flat plate narrow gap heat flow measurement test device | |
CN209606053U (en) | A kind of wind-tunnel hot exhaust interference test device | |
CN112903232A (en) | Flow regulating device for wind tunnel test of aircraft atmospheric data system | |
CN207779665U (en) | The model equipment that jet pipe is connected with shape in wind tunnel test | |
CN109799030A (en) | A kind of water-cooled pressure measurement probe suitable for high-enthalpy flow |
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 |