CN114593889B - Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area - Google Patents
Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area Download PDFInfo
- Publication number
- CN114593889B CN114593889B CN202210500371.0A CN202210500371A CN114593889B CN 114593889 B CN114593889 B CN 114593889B CN 202210500371 A CN202210500371 A CN 202210500371A CN 114593889 B CN114593889 B CN 114593889B
- Authority
- CN
- China
- Prior art keywords
- wind tunnel
- static pressure
- free jet
- speed free
- matching precision
- 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.)
- Active
Links
Images
Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/06—Measuring arrangements specially adapted for aerodynamic testing
-
- 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
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T90/00—Enabling technologies or technologies with a potential or indirect contribution to GHG emissions mitigation
Landscapes
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- General Physics & Mathematics (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
Abstract
The invention belongs to the technical field of high-speed free jet wind tunnel tests and discloses a method for obtaining static pressure matching precision of a large-range supersonic jet uniform area. The method for rapidly acquiring the static pressure matching precision of the uniform area of the large-range supersonic jet flow comprises the following steps of: arranging static pressure measuring points in the high-speed free jet flow wind tunnel; determining the total pressure of the wind tunnel stable section; starting the high-speed free jet wind tunnel in a constant total pressure operation mode; collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably; closing the high-speed free jet wind tunnel; and (6) processing data to obtain the static pressure matching precision. The method for rapidly acquiring the static pressure matching precision of the uniform area of the supersonic jet in a large range is simple and clear in thought, full in theoretical basis, capable of meeting the Mach number change requirement and the wind tunnel pressure control performance requirement, beneficial to accurately acquiring the static pressure matching precision of the supersonic jet of the high-speed free jet wind tunnel, and high in engineering application value.
Description
Technical Field
The invention belongs to the technical field of high-speed free jet wind tunnel tests, and particularly relates to a method for obtaining static pressure matching precision of a large-range supersonic jet uniform area.
Background
When a traditional high-speed free jet wind tunnel is used for supersonic speed tests, the mode of improving the running total pressure is usually adopted for blowing, and the mode can ensure that a rhombic area at the outlet of a spray pipe is uniform airflow. And the gas flow outside the diamond area and inside the jet boundary can carry out repeated expansion acceleration and compression deceleration processes, so that the quality of the flow field outside the diamond area is rapidly deteriorated. The uniform airflow in the rhombic area can be subjected to tests with small requirements on the uniform area range, such as a small attack angle air inlet channel, engine characteristics and the like, and the model scale cannot exceed the rhombic area range. Other blowing tests with low requirements on the quality of the convection field can also be carried out in a larger jet flow range. But the uniform flow field range of the diamond area is too small, so that the high-quality test requirements of a large-attack-angle air inlet channel, air inlet/engine body/engine integration, thrust vector characteristics, a large-scale model and the like are difficult to meet.
The high-speed free jet wind tunnel has the obvious advantages that the blockage degree of a model is allowed to be large, but the uniform area of the supersonic jet flow field in the traditional operation mode is small, and the function exertion of the high-speed free jet wind tunnel is limited. The adoption of the static pressure matching point mode can only adapt to the condition that the model state is unchanged or has small change, and once the model state has large change, the matching pressure of the flow field needs to be correspondingly changed at the same time to keep the supersonic flow field to have a larger uniform area range.
In order to meet the urgent need of advanced aircraft development for the flow field simulation capability of a large-range supersonic jet flow uniform area, a method for rapidly obtaining the static pressure matching precision of the large-range supersonic jet flow uniform area is urgently needed to be developed.
Disclosure of Invention
The invention aims to solve the technical problem of providing a method for rapidly obtaining the static pressure matching precision of a large-range supersonic jet flow uniform area.
The invention discloses a method for obtaining static pressure matching precision of a large-range supersonic jet flow uniform area, which is characterized in that the method is used for a high-speed free jet flow wind tunnel, the high-speed free jet flow wind tunnel sequentially comprises a spray pipe, a test cabin and a collector from front to back according to the airflow direction of the wind tunnel, and the method comprises the following steps:
s01, arranging static pressure measuring points in a high-speed free jet flow wind tunnel;
arranging a nozzle outlet static pressure measuring point at the nozzle outlet of the high-speed free jet wind tunnel, and arranging a test chamber reference point static pressure measuring point on the inner wall of the test chamber;
s02, determining total pressure of stable section of wind tunnel
；
Selecting supersonic velocity spray pipes according to the high-speed free jet wind tunnel, and determining the total pressure of the stable section of the wind tunnel according to the Mach number of the supersonic velocity spray pipes
；
S03, starting a high-speed free jet wind tunnel in a constant total pressure operation mode;
starting the high-speed free jet wind tunnel in a constant total pressure operation mode, and controlling according to the preset starting total pressure and total pressure control precision of the Mach number of the supersonic velocity spray pipe of the high-speed free jet wind tunnel;
s04, collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably;
judging that the high-speed free jet wind tunnel continuously and stably operates for T seconds after entering stable operation through total pressure stability judging conditions, and continuously and stably operating during operationThe interval is (T1, T2) and static pressure reference point static pressure of the high-speed free jet wind tunnel test cabin is continuously acquired
Static pressure at the nozzle outlet
Total pressure of stable section of wind tunnel
Obtaining a static pressure reference point static pressure array of the corresponding high-speed free jet wind tunnel test cabin
Nozzle outlet static pressure array
Total pressure array for wind tunnel stabilizing section
，
；
S05, closing the high-speed free jet flow wind tunnel;
after data acquisition is finished, closing the high-speed free jet wind tunnel;
s06, data processing is carried out, and static pressure matching precision is obtained;
finding the maximum value of static pressure reference point of high-speed free jet wind tunnel test cabin in time interval (T1, T2)
And minimum value
；
Calculating the maximum fluctuation amount of the static pressure reference point
；
Calculating the average value of the static pressure at the outlet of the spray pipe:
；
calculating the static pressure matching precision of the Mach number of the supersonic velocity spray pipe:
。
the method for quickly acquiring the static pressure matching precision of the uniform area of the large-range supersonic jet flow comprises the steps of firstly starting total pressure based on Mach number matching operation corresponding to a supersonic jet pipe, blowing in a constant total pressure starting mode, measuring and acquiring reference point static pressure of a test cabin, static pressure of an outlet of the jet pipe and total pressure of a stable section in real time through a pressure acquisition system of a high-speed free jet flow wind tunnel, carrying out total pressure control according to preset wind tunnel total pressure control precision, and shutting down after stable operation is carried out for a period of time; correspondingly extracting a test chamber static pressure array measured by a test chamber static pressure measuring point according to the collected total pressure stable operation pressure time interval, and subtracting the minimum value from the maximum value of the test chamber static pressure array to obtain a maximum fluctuation value of the test chamber static pressure; correspondingly extracting a static pressure array of the outlet of the spray pipe measured by the static pressure measuring point of the outlet of the spray pipe in the time interval, and averaging the static pressure array of the outlet of the spray pipe to obtain the average static pressure of the outlet of the spray pipe; and comparing the maximum fluctuation value of the static pressure of the test chamber with the reference static pressure at the outlet of the spray pipe to obtain the static pressure matching precision of the reference point static pressure of the test chamber and the static pressure at the outlet of the spray pipe.
The method for rapidly obtaining the static pressure matching precision of the uniform area of the large-range supersonic jet can provide guidance for the matching precision of the static pressures of the outlets of the spray pipes with different supersonic mach numbers of the high-speed free jet wind tunnel and the static pressure of the reference point of the test cabin, and is an effective method for pertinently improving the static pressure matching precision of different supersonic mach numbers; the problem that the uniformity of a flow field is poor or exceeds the pressure regulation capability of the wind tunnel due to the fact that the same static pressure matching precision is adopted due to the fact that the Mach numbers of different supersonic speeds are different is solved; the method can provide the best individualized static pressure matching precision for different supersonic mach number flow fields of the high-speed free jet wind tunnel, and further improve the flow field uniformity of the high-speed free jet wind tunnel.
The method for rapidly acquiring the static pressure matching precision of the uniform area of the supersonic jet in a large range is simple and clear in thought, full in theoretical basis, capable of meeting the Mach number change requirement and the wind tunnel pressure control performance requirement, beneficial to accurately acquiring the static pressure matching precision of the supersonic jet of the high-speed free jet wind tunnel, and high in engineering application value.
Drawings
FIG. 1 is a static pressure measuring point layout diagram in the method for obtaining the static pressure matching precision of the large-range supersonic jet flow uniform area of the invention;
FIG. 2 is a flow chart of a method of the present invention for obtaining static pressure matching accuracy for a uniform region of a wide range of supersonic jet flows;
FIG. 3 is a graph of the total pressure in the time-stabilization phase obtained in example 1.
In the figure, 1, a static pressure measuring point at the outlet of a spray pipe; 2. a test chamber reference point static pressure test point; 3. a nozzle outlet; 4. a test chamber; 5. a collector.
Detailed Description
The present invention will be described in detail below with reference to the accompanying drawings and examples.
Example 1
As shown in figure 1, the high-speed free jet wind tunnel sequentially comprises a spray pipe, a test chamber 4 and a collector 5 from front to back according to the wind tunnel airflow direction. The supersonic nozzle mach number is 1.5.
As shown in fig. 2, the implementation steps of this embodiment are as follows:
s01, arranging static pressure measuring points in a high-speed free jet flow wind tunnel;
arranging a nozzle outlet static pressure measuring point 1 at a nozzle outlet 3 of the high-speed free jet wind tunnel, and arranging a test chamber reference point static pressure measuring point 2 on the inner wall of a test chamber 4;
s02, determining total pressure of stable section of wind tunnel
；
Selecting supersonic velocity spray pipe according to high-speed free jet wind tunnel, and determining wind tunnel according to Mach number of supersonic velocity spray pipeTotal pressure of stable section
Is 192 KPa;
s03, starting a high-speed free jet wind tunnel in a constant total pressure operation mode;
starting the high-speed free jet wind tunnel in a constant total pressure operation mode, and controlling the total pressure and the total pressure according to the preset starting total pressure and total pressure control precision of the Mach number of the supersonic velocity spray pipe of the high-speed free jet wind tunnel
Controlling;
s04, collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably;
after the high-speed free jet wind tunnel is judged to enter the stable operation for about 8 seconds through the total pressure judging condition that the total pressure enters a control interval of 0.5 percent, the high-speed free jet wind tunnel continuously operates stably, and the static pressure reference point static pressure of the high-speed free jet wind tunnel test cabin is continuously collected in the operation time interval (25, 32.1) shown in figure 3
Static pressure at the nozzle outlet
Total pressure of stable section of wind tunnel
Obtaining a static pressure reference point static pressure array of the corresponding high-speed free jet wind tunnel test cabin
Nozzle outlet static pressure array
Total pressure array for wind tunnel stabilizing section
，
，
；
S05, closing the high-speed free jet flow wind tunnel;
after data acquisition is finished, closing the high-speed free jet wind tunnel;
s06, processing data to obtain static pressure matching precision;
finding the maximum value of static pressure reference point of high-speed free jet wind tunnel test cabin in time interval (25, 32.1)
And minimum value
；
Calculating the maximum fluctuation amount of the static pressure reference point
；
Calculating the average value of the static pressure at the outlet of the spray pipe:
；
calculating the static pressure matching precision of the Mach number of the supersonic velocity spray pipe:
。
although the embodiments of the present invention have been disclosed above, it is not limited to the applications listed in the description and the embodiments, but it can be applied to various fields suitable for the present invention. Additional modifications and refinements will readily occur to those skilled in the art without departing from the principles of the present invention, and the present invention is not limited to the specific details and illustrations shown and described herein.
Claims (1)
1. The method for obtaining the static pressure matching precision of the uniform area of the supersonic jet flow in a large range is characterized in that the method is used for a high-speed free jet flow wind tunnel, and the high-speed free jet flow wind tunnel sequentially comprises a spray pipe, a test cabin (4) and a collector (5) from front to back according to the airflow direction of the wind tunnel, and the method comprises the following steps of:
s01, arranging static pressure measuring points in a high-speed free jet flow wind tunnel;
arranging a nozzle outlet static pressure measuring point (1) at a nozzle outlet (3) of the high-speed free jet wind tunnel, and arranging a test chamber reference point static pressure measuring point (2) on the inner wall of a test chamber (4);
s02, determining total pressure of stable section of wind tunnel
；
Selecting supersonic velocity spray pipes according to the high-speed free jet wind tunnel, and determining the total pressure of the stable section of the wind tunnel according to the Mach number of the supersonic velocity spray pipes
；
S03, starting a high-speed free jet wind tunnel in a constant total pressure operation mode;
starting the high-speed free jet wind tunnel in a constant total pressure operation mode, and controlling according to the preset starting total pressure and total pressure control precision of the Mach number of the supersonic velocity spray pipe of the high-speed free jet wind tunnel;
s04, collecting relevant flow field parameters after the high-speed free jet wind tunnel operates stably;
and (3) judging whether the high-speed free jet wind tunnel enters stable operation through the total pressure judging condition, continuously and stably operating for T seconds, and continuously acquiring the static pressure reference point static pressure of the high-speed free jet wind tunnel test cabin in the operating time interval (T1, T2)
Static pressure at the nozzle outlet
Total pressure of stable section of wind tunnel
Obtaining a static pressure reference point static pressure array of the corresponding high-speed free jet wind tunnel test cabin
Nozzle outlet static pressure array
Total pressure array for wind tunnel stabilizing section
，
；
S05, closing the high-speed free jet flow wind tunnel;
after data acquisition is finished, closing the high-speed free jet wind tunnel;
s06, data processing is carried out, and static pressure matching precision is obtained;
finding the maximum value of static pressure reference point of high-speed free jet wind tunnel test cabin in time interval (T1, T2)
And minimum value
；
Calculating the maximum fluctuation amount of the static pressure reference point
；
Calculating the average value of the static pressure at the outlet of the spray pipe:
；
calculating the static pressure matching precision of the Mach number of the supersonic velocity spray pipe:
；
the method provides guidance for matching precision of static pressures at the outlet of the nozzle with different supersonic mach numbers of the high-speed free jet wind tunnel and static pressure at the reference point of the test chamber, and is an effective method for pertinently improving the matching precision of the static pressures with different supersonic mach numbers; the problem that the uniformity of a flow field is poor or exceeds the pressure regulation capability of the wind tunnel due to the fact that the same static pressure matching precision is adopted for different supersonic mach numbers is solved; the method provides individualized static pressure matching precision for different supersonic mach number flow fields of the high-speed free jet wind tunnel, and further improves the uniformity of the flow field of the high-speed free jet wind tunnel.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210500371.0A CN114593889B (en) | 2022-05-10 | 2022-05-10 | Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210500371.0A CN114593889B (en) | 2022-05-10 | 2022-05-10 | Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN114593889A CN114593889A (en) | 2022-06-07 |
| CN114593889B true CN114593889B (en) | 2022-08-09 |
Family
ID=81812561
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210500371.0A Active CN114593889B (en) | 2022-05-10 | 2022-05-10 | Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN114593889B (en) |
Families Citing this family (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116296226A (en) * | 2023-05-23 | 2023-06-23 | 中国航空工业集团公司沈阳空气动力研究所 | Flow field control method for 1 meter-level direct current temporary flushing blowing guiding type hypersonic wind tunnel |
| CN117647374B (en) * | 2024-01-25 | 2024-04-16 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining migration speed of high-speed jet shear layer based on dynamic pressure data |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7401505B1 (en) * | 2007-01-09 | 2008-07-22 | The United States Of America As Represented By The Secretary Of The Navy | Low cost wind tunnel for supersonic and hypersonic aerothermal testing |
| CN111006843A (en) * | 2019-12-04 | 2020-04-14 | 中国航天空气动力技术研究院 | Continuous variable speed pressure method of temporary impulse type supersonic wind tunnel |
| CN112747887A (en) * | 2020-12-25 | 2021-05-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-step presetting method for opening degree of regulating valve suitable for hypersonic wind tunnel |
| CN114061891A (en) * | 2022-01-18 | 2022-02-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Downward-blowing injection type static pressure matching control method for large-size open jet wind tunnel |
Family Cites Families (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPH087109B2 (en) * | 1991-10-09 | 1996-01-29 | 川崎重工業株式会社 | Pressure control device for blow-out wind tunnel |
| DE102005045079B4 (en) * | 2005-09-21 | 2010-02-25 | Infineon Technologies Ag | Concept for testing a pressure sensor and a nozzle |
| US7302839B1 (en) * | 2006-06-22 | 2007-12-04 | Cessna Aircraft Company | Method and system for gathering pressure signature data using a scaled model in a wind tunnel |
| RU2339928C1 (en) * | 2007-03-19 | 2008-11-27 | Институт теоретической и прикладной механики им. С.А. Христиановича СО РАН (ИТПМ СО РАН) | Calibration aerodynamic model for determining systematic errors and method of determining systematic errors |
| CN106599419B (en) * | 2016-12-02 | 2019-07-12 | 中国船舶工业系统工程研究院 | Naval vessel stern flow field numerical simulation and the control methods of wind tunnel test aggregation of data |
| CN111339681B (en) * | 2020-03-23 | 2020-11-06 | 中国空气动力研究与发展中心计算空气动力研究所 | Nozzle outlet parameter matching method for simulating engine gas medium jet flow aerodynamic interference effect by adopting air medium |
| CN112834161B (en) * | 2021-02-04 | 2024-02-23 | 中国空气动力研究与发展中心空天技术研究所 | Wind tunnel measurement data processing method based on feature extraction |
| CN114184349B (en) * | 2022-02-15 | 2022-04-15 | 中国空气动力研究与发展中心高速空气动力研究所 | Method for obtaining supersonic jet static operation pressure matching point of jet wind tunnel |
-
2022
- 2022-05-10 CN CN202210500371.0A patent/CN114593889B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7401505B1 (en) * | 2007-01-09 | 2008-07-22 | The United States Of America As Represented By The Secretary Of The Navy | Low cost wind tunnel for supersonic and hypersonic aerothermal testing |
| CN111006843A (en) * | 2019-12-04 | 2020-04-14 | 中国航天空气动力技术研究院 | Continuous variable speed pressure method of temporary impulse type supersonic wind tunnel |
| CN112747887A (en) * | 2020-12-25 | 2021-05-04 | 中国空气动力研究与发展中心超高速空气动力研究所 | Multi-step presetting method for opening degree of regulating valve suitable for hypersonic wind tunnel |
| CN114061891A (en) * | 2022-01-18 | 2022-02-18 | 中国空气动力研究与发展中心高速空气动力研究所 | Downward-blowing injection type static pressure matching control method for large-size open jet wind tunnel |
Non-Patent Citations (4)
| Title |
|---|
| 2.4m跨声速风洞大振幅动态试验技术;马上 等;《空气动力学学报》;20191215;第37卷(第06期);第998-1003页 * |
| Derivation and validation of wind tunnel free-flight similarity law for store separation from aircraft;Fei Xue, Yuchao Wang, Han Qin;《Aerospace Science and Technology》;20191205;第97卷;第1-9页 * |
| 基于神经网络的风洞马赫数预测控制仿真研究;金志伟,杨兴锐,苏北辰;《兵工自动化》;20160315;第35卷(第3期);第59-60页 * |
| 大型低温高雷诺数风洞及其关键技术综述;廖达雄 等;《实验流体力学》;20140415(第02期);第1-6页 * |
Also Published As
| Publication number | Publication date |
|---|---|
| CN114593889A (en) | 2022-06-07 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN114593889B (en) | Method for obtaining static pressure matching precision of large-range supersonic jet flow uniform area | |
| CN114184349B (en) | Method for obtaining supersonic jet static operation pressure matching point of jet wind tunnel | |
| CN114608784B (en) | Method for obtaining dynamic running pressure matching point of jet flow in jet wind tunnel through ultrasonic velocity jet flow | |
| CN106989891B (en) | Acceleration self-starting experimental method for hypersonic air inlet | |
| CN111914365A (en) | Variable-cycle engine modeling method and variable-cycle engine component level model | |
| CN114279714B (en) | Aeroengine turbine test bed under high altitude and low Reynolds number, simulation method and application | |
| CN110647052B (en) | Variable cycle engine mode switching self-adaptive identity card model construction method | |
| CN114018532B (en) | Test method for continuous variable total pressure of hypersonic wind tunnel | |
| CN116480618B (en) | Large continuous transonic wind tunnel axial flow compressor test device and method | |
| CN113029573B (en) | Low-Reynolds-number plane cascade high-altitude flow simulation device | |
| CN111780949B (en) | CFD analysis-based total pressure correction method for high-speed air inlet channel precursor wind tunnel experiment | |
| Cubbison et al. | Effect of porous bleed in a high performance axisymmetric, mixed compression inlet at Mach 2.50 | |
| CN114608785B (en) | Method for obtaining static pressure matching accuracy of uniform area of large-range supersonic jet flow field | |
| CN110043370B (en) | Air flow measuring method of turbofan engine core machine | |
| CN114013666B (en) | Active stability augmentation control method and device for aero-engine | |
| Barker et al. | Influence of compressor exit conditions on combustor annular diffusers, part 1: diffuser performance | |
| CN114608792B (en) | Method for measuring uniform region of sub-transonic jet flow field of high-speed jet wind tunnel by short-shaft probe | |
| CN111487029B (en) | High-speed wind tunnel air inlet passage throttling cone with accurately controlled flow and test throttling device | |
| CN111523220A (en) | Fan and compressor rotating-static interference broadband noise rapid prediction method considering flow influence | |
| Cubbison et al. | Performance characteristics from Mach 2.58 to 1.98 of an axisymmetric mixed-compression inlet system with 60-percent internal contraction | |
| CN112964448B (en) | Airflow mixer for plane blade grid high-altitude flow simulation device | |
| Sooriyakumaran | Experimental study of profile losses in three transonic turbine cascades | |
| CN113076610A (en) | Design method of binary adjustable air inlet channel | |
| CN114608791B (en) | Method for obtaining high-speed free jet wind tunnel supersonic jet flow field diamond area range | |
| Kussoy et al. | Comparison of Performance of Two Aerodynamically Similar 14-inch-diameter Single-stage Compressor Rotors of Different Chord Length |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |