CN115950493B - Flow testing system and method suitable for subsonic flow channel - Google Patents
Flow testing system and method suitable for subsonic flow channel Download PDFInfo
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Abstract
The invention discloses a flow test system and a flow test method suitable for subsonic flow channels. And controlling the Mach number of the outlet of the air inlet channel by adjusting the outlet area of the throttling module and the downstream pressure, and forming a supersonic flow field structure after the throttling module. The quick valve at the vacuum cavity is closed, fluid is rectified by the rear rectifying section and enters the stagnation module, and supersonic airflow is stopped. And obtaining the flow of the subsonic flow channel through monitoring the pressure change conversion in the cavity. The invention has simple structure, small size, high response speed and high measurement precision, needs few pressure measuring points, avoids the choking of flow test methods such as standard flowmeter, traditional meter-shaped harrow and the like on experimental flow channels, has the measurement precision insensitive to the non-uniformity of the air flow in the flow channels, and is suitable for the flow measurement of complex internal flow devices such as air inlets, diffusers and the like with subsonic flow.
Description
Technical Field
The invention relates to the field of aerodynamic experiment tests, in particular to a flow test system and a flow test method for an air inlet channel and other internal flow devices working in a subsonic speed range.
Background
In the development process of the air suction type propulsion system, a ground experiment is a key link in the early stage, individual tests are required to be carried out on all pneumatic components, and the obtained performance curve of the components provides data and guidance for the follow-up wind tunnel experiment and the full-machine experiment. The air inlet channel is used as one of key pneumatic components of the air suction type propulsion system, and has the functions of capturing and adjusting the flow of the propulsion system, converting and utilizing the kinetic energy of incoming flow and the like, so that the thrust, the working efficiency, the working envelope and the like of the propulsion system are directly influenced, and the accuracy of the ground experimental data of the air inlet channel and the testing range of the working condition are very important for the research and development of the propulsion system. During the course of the experiment, the outlet flow of the inlet is typically tested to reflect its ability to capture incoming flow. Common subsonic flow channel flow measuring methods comprise devices such as an orifice plate flow meter, a float flow meter, a turbine flow meter, a vortex shedding flow meter, a venturi flow meter and the like. The orifice plate flowmeter adopts flange connection and ensures the precision through an acute angle line of an inner hole, so that the problems of flow leakage and test precision reduction under long-term use cannot be avoided, and larger maintenance workload is required; when the float flowmeter is used for testing fluid flow different from factory calibration fluid, such as different fluid density and viscosity, the flow deviates from the original graduation value, and conversion correction is needed, so that the use is relatively complex; the vortex shedding flowmeter is sensitive to vibration of an experimental model, and the high subsonic velocity flow experiment can have a large influence on the accuracy; turbine flowmeters are not suitable for use with media having relatively high viscosity or excessive impurities. Besides, because the inside of the flow meter contains large-size parts, on one hand, the response speed of the flow meter is slow due to the inertial movement of the parts, and on the other hand, the air flow is easy to form choking in the flow passage, so the flow meter is not suitable for the flow test of the air inlet passage. The venturi flowmeter is different from the standard flowmeter, large-size parts are not arranged in the flow channel, the response is rapid, but because the dense flow function at the throat is maximum, the flushing and abrasion of the fluid to the throat are serious, the long-term measurement accuracy cannot be ensured, and the structural length of the classical venturi flowmeter must be manufactured according to the specification, so that the flow measurement range of the classical venturi flowmeter is limited, the maximum flow ratio and the minimum flow ratio are very small and are generally between 3 and 5, and the venturi flowmeter is difficult to meet the flow measurement with large flow change range.
In another commonly used flow test method, 8 total pressure rakes are uniformly distributed on a measurement section, 5 total pressure probes are arranged on each rake according to equal torus integration cloth, and flow can be obtained according to each unit integration by using the measurement results of the probes, however, because the total pressure probes are limited, the measurement accuracy of the meter-shaped rake needs to be good, and the distortion cannot be too large, and the section flow uniformity is good, otherwise, the error is large.
In summary, for the air inlet channel flow test experiment, the existing flowmeter cannot meet the requirements of quick response, large flow test range, prevention of inner flow channel congestion and the like, so for the subsonic flow channel flow test experiment, how to realize quick response of the test system, high measurement accuracy, easy maintenance of the device, large flow measurement range and prevention of inner flow channel congestion are key problems to be solved by the invention.
Disclosure of Invention
The invention aims to: the invention provides a flow test system suitable for a subsonic flow channel, aiming at the flow test experiment of the subsonic flow channel, the invention aims at realizing the purposes of quick response, high measurement precision, easy maintenance of a device, large flow measurement range and avoidance of congestion of an internal flow channel.
In order to achieve the above purpose, the technical scheme adopted by the invention is as follows:
the flow testing system suitable for the subsonic flow channel comprises a standard model of the subsonic flow channel, a transition section, a rectifying section, a throttling module, a stagnation module and a vacuum cavity; the standard model, the transition section and the rectifying section are sequentially connected, and the internal surfaces of the standard model, the transition section and the rectifying section are sequentially tangent to form an internal flow passage of the flow test system, and the cross-sectional areas of the internal flow passage are equal; the rectifying section comprises a front rectifying section and a rear rectifying section; a rectification grille is arranged in the rear rectification section so that all parameters of the section airflow are uniformly distributed; the throttling module rectifying section is arranged inside and between the front rectifying section and the rear rectifying section; the stagnation module is positioned at the downstream of the rear rectifying section, the whole stagnation module is a cavity, and the joint of the stagnation module and the rear rectifying section is a sudden expansion runner; the vacuum cavity is positioned at the downstream of the stagnation module, a sudden shrinkage runner is arranged at the joint of the vacuum cavity and the stagnation module, and a quick valve is arranged at the joint of the vacuum cavity and the stagnation module; the flow test system is used for collecting the total pressure signal of the first measuring point and the static pressure signal of the second measuring point at the outlet of the standard model, the total pressure signal of the third measuring point and the static pressure signal of the fourth measuring point at the downstream of the throttling module, the dynamic pressure signals of a plurality of fifth measuring points and the temperature signals of the sixth measuring points which are preset on the inner wall surface of the stagnation module; the first measuring point and the second measuring point are positioned on the same section of the standard model, the first measuring point is positioned on the inner wall surface of the standard model, and the second measuring point is positioned in the cavity of the standard model; the third measuring point and the fourth measuring point are positioned on the same section of the throttling module, the third measuring point is positioned on the cavity of the throttling module, and the fourth measuring point is positioned on the inner wall surface of the throttling module; the fifth measuring points are distributed on the inner wall surface of the stagnation module and used for measuring dynamic pressure values received by all positions of the inner wall surface of the stagnation module, and the sixth measuring points are located in the stagnation module and used for measuring temperature values in the stagnation module.
Furthermore, the standard model is an equal-area circular pipeline with a lip at the front end, and the inner profile of the lip is designed as a lemniscate.
Further, the upstream of the transition section is connected with a standard model, and the downstream is connected with the front rectifying section.
Further, the front rectifying section, the rear rectifying section, the throttling module, the stagnation module, the vacuum cavity and the quick valve are all positioned outside the wind tunnel; the length of the front rectifying section is not less than 5 times of the diameter of the inner profile of the flow passage.
Further, the throttle module is composed of a butterfly valve, the opening and closing piece of the throttle module is a disc-shaped butterfly plate and rotates around the valve shaft to open and close or adjust the area of a throttle channel, so that the Mach number of an outlet of the experimental model is controlled, and an ultrasonic flow field is formed at the throttle channel.
Further, the stagnation module is a cavity with larger size, and the front and the rear of the stagnation module are respectively provided with a through round hole which is respectively connected with the rear rectifying section and the vacuum cavity. The diameters of the front and rear through round holes are respectively determined by the inner diameter of the flow passage of the rear rectifying section and the inner diameter of the flow passage of the vacuum cavity.
Further, the quick valve is arranged between the stagnation module and the vacuum cavity, and is always opened before the flow field is established, so that the front-back pressure drop ratio of the throttling module is large enough, and the downstream of the throttling module is the supersonic flow field after the flow field is normally established.
Furthermore, all pressure signals are collected by adopting a high-frequency response miniature dynamic pressure sensor, and the sensor is close to the measuring point and has a distance of not more than 50mm.
Furthermore, the measuring point adopts a high-precision thermocouple to monitor the temperature signal in the stagnation module.
The invention also provides a testing method using the flow testing system suitable for the subsonic flow channel, which comprises the following steps:
(1) In order to improve the measurement accuracy, firstly, calibrating a flow test system suitable for the subsonic flow channel, and carrying out a calibration experiment by using a standard model; arranging a pressure measurement near an outlet of the standard model and downstream of the butterfly valve;
(2) After the flow field in the channel is established, the total pressure of the first measuring point and the static pressure of the second measuring point in the flow test system are used for obtaining the model outlet Mach number according to the total static pressure relation:
Wherein p * is the total pressure at the first measuring point, p is the static pressure at the second measuring point, and M is the standard model outlet Mach number; if the Mach number at the outlet does not reach the set value, further adjusting the opening of the butterfly valve until the Mach number at the outlet is met;
(3) Monitoring the total pressure of a third measuring point and the static pressure of a fourth measuring point at the downstream of the throttling module, and obtaining the Mach number behind the throttling module through the total static pressure relation, wherein if the total static pressure relation is larger than 1, the fact that a supersonic flow field is established behind the throttling module is indicated, downstream disturbance is not transmitted to a standard model outlet, and if the total static pressure is smaller than 1, the pressure of a vacuum cavity is changed, and then the front-rear pressure drop ratio of the throttling module is changed until the Mach number at the downstream of the throttling module is larger than 1;
(4) Closing the quick valve, enabling the air flow of the internal flow field to be stagnated, and calculating the mass flow according to a gas state equation and a flow calculation formula by measuring dynamic changes of static pressures p' of a plurality of fifth measuring points on the wall surface of the stagnation module and temperatures of sixth measuring points in the stagnation module:
Wherein p' is the static pressure of a measuring point at the wall surface of the stagnation module, R is a gas constant, V is the volume of the stagnation module, T is time, and T is the temperature in the stagnation module.
According to the invention, the supersonic flow field is formed at the downstream of the fluid throttling module through the large drop ratio formed by the downstream vacuum cavity, so that downstream disturbance is prevented from propagating upstream, and subsonic flow field in the air inlet channel is prevented from being influenced. The fluid is rectified before the air flow is stagnant through the rectification grille, so that the pressure change in the stagnation module is uniform. The air flow is quickly stopped by the quick valve and the stopping module, and the outlet flow of the air inlet channel is obtained through conversion by monitoring the pressure change in the stopping module, so that the problem that the conventional flowmeter is blocked to an experimental flow channel is also avoided. All pressure signals in the whole flow test system are collected by using the high-frequency response miniature dynamic pressure sensor, so that the response speed of the test system is ensured. The invention has simple structure, small size, high response speed and high measurement precision, and the throttle module can adjust the throttle degree according to the pipe flow speed required by the experiment, so the invention has wide range of applicable working conditions; the required pressure measuring points are few, so that congestion caused by flow testing methods such as a standard flowmeter, a traditional meter-shaped harrow and the like to an experimental flow passage is avoided, the measuring accuracy is insensitive to the non-uniformity of the air flow in the flow passage, and the flow meter is particularly suitable for flow measurement of complex internal flow devices such as an air inlet passage with subsonic velocity and a diffuser.
Drawings
FIG. 1 is a schematic diagram of a subsonic flow channel flow test system according to the present invention.
Detailed Description
The invention discloses a flow testing system and a flow testing method suitable for subsonic flow channels. Referring to fig. 1, a flow testing system suitable for a subsonic flow channel includes a standard model 1, a transition section 2, a rectifying section, a throttling module 7, a stagnation module 5 and a pressure chamber 6. The standard model 1, the transition section 2 and the rectifying section are sequentially connected, the internal profile surfaces of the components are sequentially tangent to form an internal flow passage of the flow test system, the cross-sectional areas of the internal flow passage are equal, and the cross-sectional shapes of the internal flow passage are circular. The rectifying section comprises a front rectifying section 3 and a rear rectifying section 4. The throttle module 7 is located in the rectifying section and between the front rectifying section 3 and the rear rectifying section 4. And a rectification grille 8 is arranged in the rear rectification section 4 so that all parameters of the section airflow are uniformly distributed. The stagnation module 5 is positioned at the downstream of the rear rectifying section 4, the whole stagnation module 5 is a cavity, and the joint of the stagnation module 5 and the rear rectifying section 4 is a sudden expansion runner. The vacuum cavity 6 is positioned at the downstream of the stagnation module 5, and a junction with the stagnation module 5 is a contracted flow passage and is provided with a quick valve 9. The signals to be collected by the flow test system comprise a total pressure signal of a first measuring point 11 and a static pressure signal of a second measuring point 10 at the outlet of a standard model 1, a total pressure signal of a third measuring point 13 and a static pressure signal of a fourth measuring point 11 at the downstream of a throttling module 7, dynamic pressure signals of a plurality of fifth measuring points (the three reference numerals of the fifth measuring points are 14, 15 and 16 in the figure 1) preset on the inner wall surface of a stagnation module 5 and temperature signals of a sixth measuring point 17; the first measuring point 11 and the second measuring point 10 are positioned on the same section of the standard model 1, the first measuring point 11 is positioned on the inner wall surface of the standard model 1, and the second measuring point 10 is positioned in the cavity of the standard model 1; the third measuring point 13 and the fourth measuring point 12 are positioned on the same section of the throttling module 7, the third measuring point 13 is positioned on the cavity of the throttling module 7, and the fourth measuring point 12 is positioned on the inner wall surface of the throttling module 7; the fifth measuring points are distributed on the inner wall surface of the stagnation module 5 to measure dynamic pressure values received by all positions of the inner wall surface of the stagnation module 5, and the sixth measuring points 17 are located in the stagnation module 5 to measure temperature values inside the stagnation module 5.
Referring to fig. 1, in the experimental process, after the internal flow field is established, by monitoring the pressure p * of the total pressure measuring point 11 and the pressure p of the static pressure measuring point 10 at the outlet of the standard model 1, the outlet mach number is obtained according to the total static pressure relation:
If the Mach number at the outlet does not reach the set value, further adjusting the opening of the butterfly valve until the opening is met; then monitoring pressure signals of a third measuring point 13 and a fourth measuring point 12 of the throttling module 7, obtaining the Mach number at the downstream of the throttling module 7 through a total static pressure relation, if the total static pressure relation is larger than 1, indicating that a supersonic flow field is established at the downstream of the throttling module 7, and if the total static pressure relation is smaller than 1, continuously changing the pressure of the vacuum cavity 6 to further change the front-rear pressure drop ratio of the throttling module 7 until the Mach number at the downstream of the throttling module 7 is larger than 1; then the quick valve 9 is closed, the air flow of the internal flow field is stopped, and the mass flow is calculated according to a gas state equation and a flow calculation formula by measuring the static pressure p' change of a fifth measuring point at the wall surface of the throttling module 7 and the temperature of a sixth measuring point 17 in the stopping module:
Wherein p' is the static pressure of a measuring point at the wall surface of the stagnation module, R is a gas constant, V is the volume of the stagnation module, T is time, and T is the temperature in the stagnation module.
Claims (9)
1. The flow testing system suitable for the subsonic flow channel comprises a standard model (1) of the subsonic flow channel, a transition section (2), a rectifying section, a throttling module (7), a stagnation module (5) and a vacuum cavity (6); the standard model (1), the transition section (2) and the rectifying section are sequentially connected, and inner surfaces of the standard model (1), the transition section (2) and the rectifying section are sequentially tangent to form an inner flow passage of the flow test system, and the cross-sectional areas of the inner flow passage are equal; the rectifying section comprises a front rectifying section (3) and a rear rectifying section (4); a rectifying grid (8) is arranged in the rear rectifying section (4) so that all parameters of the section airflow are uniformly distributed; the throttling module (7) is positioned inside the rectifying section and between the front rectifying section (3) and the rear rectifying section (4); the stagnation module (5) is positioned at the downstream of the rear rectifying section (4), the whole stagnation module (5) is a cavity, and the joint of the stagnation module (5) and the rear rectifying section (4) is a sudden expansion runner; the vacuum cavity (6) is positioned at the downstream of the stagnation module (5), a junction of the vacuum cavity (6) and the stagnation module (5) is a contracted flow passage, and a rapid valve (9) is arranged at the junction of the vacuum cavity (6) and the stagnation module (5); the flow test system is used for collecting the total pressure signal of a first measuring point (11) and the static pressure signal of a second measuring point (10) at the outlet of the standard model (1), the total pressure signal of a third measuring point (13) and the static pressure signal of a fourth measuring point (12) at the downstream of the throttling module (7), and the dynamic pressure signals of a plurality of fifth measuring points and the temperature signals of a sixth measuring point which are preset on the inner wall surface of the stagnation module; the first measuring point (11) and the second measuring point (10) are positioned on the same section of the standard model (1), the first measuring point (11) is positioned on the inner wall surface of the standard model (1), and the second measuring point (10) is positioned in the cavity of the standard model (1); the third measuring point (13) and the fourth measuring point (12) are positioned on the same section of the throttling module (7), the third measuring point (13) is positioned on the cavity of the throttling module (7), and the fourth measuring point (12) is positioned on the inner wall surface of the throttling module (7); the fifth measuring points are distributed on the inner wall surface of the stagnation module (5) and used for measuring dynamic pressure values received by all positions of the inner wall surface of the stagnation module (5), and the sixth measuring points (17) are positioned in the stagnation module (5) and used for measuring temperature values in the stagnation module; the throttle module (7) is composed of butterfly valves, the opening and closing piece of the throttle module (7) is a disc-shaped butterfly plate, and the butterfly plate rotates around a valve shaft to open and close or adjust the area of a throttle channel, so that the Mach number of an outlet of an experimental model is controlled, and an ultrasonic flow field is formed at the throttle channel.
2. The flow test system for subsonic flow channels of claim 1, wherein: the standard model is an equal-area circular pipeline with a lip at the front end, and the front end of the lip is designed as a double-button line.
3. The flow test system for subsonic flow channels of claim 1, wherein: the upstream of the transition section (2) is connected with the standard model (1), and the downstream is connected with the front rectifying section (3).
4. The flow test system for subsonic flow channels of claim 1, wherein: the front rectifying section (3), the rear rectifying section (4), the throttling module (7), the stagnation module (5), the vacuum cavity (6) and the quick valve (9) are all positioned outside the wind tunnel; the length of the front rectifying section (3) is not less than 5 times of the diameter of the inner profile of the flow passage.
5. The flow test system for subsonic flow channels of claim 1, wherein: the stagnation module (5) is a cavity with larger size, and a through round hole is respectively arranged at the front and the rear and is respectively connected with the rear rectifying section (4) and the vacuum cavity (6); the diameters of the front and rear through round holes are respectively determined by the inner diameter of the flow channel of the rear rectifying section (4) and the inner diameter of the flow channel of the vacuum cavity (6).
6. The flow test system for subsonic flow channels of claim 1, wherein: the quick valve (9) is positioned between the stagnation module (5) and the vacuum cavity (6), and before the flow field is established, the quick valve (9) is always kept open, so that the front-back pressure drop ratio of the throttling module (7) is large enough, and after the flow field is normally established, the downstream of the throttling module (7) is an ultrasonic flow field.
7. The flow test system for subsonic flow channels of claim 1, wherein: all pressure signals are collected by adopting a high-frequency response miniature dynamic pressure sensor, and the sensor is close to the measuring point and has a distance not exceeding 50mm.
8. The flow test system for subsonic flow channels of claim 1, wherein: and the sixth measuring point (17) adopts a high-precision thermocouple to monitor the temperature signal in the stagnation module.
9. A testing method using the flow testing system for subsonic flow channels according to any one of claims 1 to 8, characterized by comprising the steps of:
(1) In order to improve the measurement accuracy, firstly, calibrating a flow test system suitable for the subsonic flow channel, and carrying out a calibration experiment by using a standard model (1); arranging a pressure measurement near the outlet of the standard model (1) and downstream of the butterfly valve;
(2) After the flow field in the channel is established, the total pressure of a first measuring point (11) and the static pressure of a second measuring point (10) in the flow test system are used for obtaining the model outlet Mach number according to a total static pressure relational expression:
Wherein/> The total pressure at the first measuring point (11), p is the static pressure at the second measuring point (10), and M is the outlet Mach number of the standard model (1); if the Mach number at the outlet does not reach the set value, further adjusting the opening of the butterfly valve until the Mach number at the outlet is met;
(3) Monitoring the total pressure of a third measuring point (13) and the static pressure of a fourth measuring point (12) at the downstream of the throttling module (7), and obtaining the Mach number behind the throttling module (7) through a total static pressure relation, wherein if the total static pressure relation is larger than 1, the fact that a supersonic flow field is established behind the throttling module (7) is indicated, downstream disturbance is not transmitted to a standard model outlet, if the total static pressure is smaller than 1, the pressure of a vacuum cavity (6) is changed, and then the front-rear drop pressure ratio of the throttling module (7) is changed until the Mach number at the downstream of the throttling module (7) is larger than 1;
(4) Closing the quick valve, allowing the air flow of the internal flow field to be stagnated, and measuring the static pressure of a plurality of fifth measuring points on the wall surface of the stagnation module The temperature at a sixth measuring point (17) in the stagnation module, and calculating the mass flow according to a gas state equation and a flow calculation formula:
Wherein/> The static pressure is measured at the wall surface of the stagnation module, R is a gas constant, V is the volume of the stagnation module, T is time, and T is the temperature in the stagnation module.
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Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103149010A (en) * | 2013-02-22 | 2013-06-12 | 中国人民解放军国防科学技术大学 | NPLS measurement system and method for air inlet channel flow field based on high-supersonic-velocity pulse wind tunnel |
| CN105157948A (en) * | 2015-09-14 | 2015-12-16 | 南京航空航天大学 | Flow test system suitable for supersonic/hypersonic channel and test method |
| CN108168832A (en) * | 2016-12-08 | 2018-06-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of throat structure for improving tube wind tunnel experiment Reynolds number |
| KR101869648B1 (en) * | 2017-03-23 | 2018-06-21 | 국방과학연구소 | Flow rate calibration device for wind tunnel model and method thereof |
| CN111006841A (en) * | 2019-11-29 | 2020-04-14 | 中国航天空气动力技术研究院 | Wide-area air inlet pressure regulating system for hypersonic wind tunnel |
| CN111006840A (en) * | 2019-11-29 | 2020-04-14 | 中国航天空气动力技术研究院 | Hypersonic wind tunnel vacuum pressure air inlet pressure regulating method |
| CN113176065A (en) * | 2021-04-29 | 2021-07-27 | 台州学院 | Negative pressure type Laval nozzle flow characteristic experiment system and experiment method thereof |
| CN113701987A (en) * | 2021-08-26 | 2021-11-26 | 中国科学院力学研究所 | High-pressure gas flow control device for wind tunnel test |
| CN115290291A (en) * | 2022-06-14 | 2022-11-04 | 南京航空航天大学 | Experimental device for simulating boundary layer leakage flow and subsonic velocity outflow coupling effect |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9910448B2 (en) * | 2013-03-14 | 2018-03-06 | Christopher Max Horwitz | Pressure-based gas flow controller with dynamic self-calibration |
| JP6533878B1 (en) * | 2017-08-09 | 2019-06-19 | Ckd株式会社 | Flowmeter |
-
2022
- 2022-12-21 CN CN202211646660.8A patent/CN115950493B/en active Active
Patent Citations (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103149010A (en) * | 2013-02-22 | 2013-06-12 | 中国人民解放军国防科学技术大学 | NPLS measurement system and method for air inlet channel flow field based on high-supersonic-velocity pulse wind tunnel |
| CN105157948A (en) * | 2015-09-14 | 2015-12-16 | 南京航空航天大学 | Flow test system suitable for supersonic/hypersonic channel and test method |
| CN108168832A (en) * | 2016-12-08 | 2018-06-15 | 中国航空工业集团公司沈阳空气动力研究所 | A kind of throat structure for improving tube wind tunnel experiment Reynolds number |
| KR101869648B1 (en) * | 2017-03-23 | 2018-06-21 | 국방과학연구소 | Flow rate calibration device for wind tunnel model and method thereof |
| CN111006841A (en) * | 2019-11-29 | 2020-04-14 | 中国航天空气动力技术研究院 | Wide-area air inlet pressure regulating system for hypersonic wind tunnel |
| CN111006840A (en) * | 2019-11-29 | 2020-04-14 | 中国航天空气动力技术研究院 | Hypersonic wind tunnel vacuum pressure air inlet pressure regulating method |
| CN113176065A (en) * | 2021-04-29 | 2021-07-27 | 台州学院 | Negative pressure type Laval nozzle flow characteristic experiment system and experiment method thereof |
| CN113701987A (en) * | 2021-08-26 | 2021-11-26 | 中国科学院力学研究所 | High-pressure gas flow control device for wind tunnel test |
| CN115290291A (en) * | 2022-06-14 | 2022-11-04 | 南京航空航天大学 | Experimental device for simulating boundary layer leakage flow and subsonic velocity outflow coupling effect |
Non-Patent Citations (1)
| Title |
|---|
| 亚声速S弯进气道研究的新进展;黄河峡 等;《推进技术》;20201231;第41卷(第12期);第2641-2656页 * |
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