CN116147882B - Low-speed wind tunnel flow field parameter measuring device and method - Google Patents
Low-speed wind tunnel flow field parameter measuring device and method Download PDFInfo
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- CN116147882B CN116147882B CN202310435970.3A CN202310435970A CN116147882B CN 116147882 B CN116147882 B CN 116147882B CN 202310435970 A CN202310435970 A CN 202310435970A CN 116147882 B CN116147882 B CN 116147882B
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- G—PHYSICS
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- 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
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D21/00—Measuring or testing not otherwise provided for
- G01D21/02—Measuring two or more variables by means not covered by a single other subclass
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- 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
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Abstract
A low-speed wind tunnel flow field parameter measuring device and method belong to the technical field of wind tunnel tests. The invention comprises two measuring rakes and a static pressure plate, wherein the two measuring rakes are respectively arranged at two ends of a pressure measuring pipeline, the static pressure plate is arranged in the middle of the pressure measuring pipeline, a first pressure difference sensor, a second pressure difference sensor, a third pressure difference sensor and a fourth pressure difference sensor are arranged on the pressure measuring pipeline, the measuring rakes are used for measuring the total pressure and the total temperature and humidity of air flow in a stable section, and the static pressure of the wall of a contracted section is obtained through a loop formed by the static pressure plate, the pressure measuring pipeline and the pressure sensor. The invention aims to provide a low-speed wind tunnel flow field parameter measuring device and a low-speed wind tunnel flow field parameter measuring method which are distributed and installed in a wind tunnel stabilizing section and a shrinkage section, so that the problem of accurate measurement of a test incoming flow field parameter in a low-speed wind tunnel is solved.
Description
Technical Field
The invention relates to a low-speed wind tunnel flow field parameter measuring device and method, and belongs to the technical field of wind tunnel tests.
Background
Wind tunnel tests, like scientific tests in other fields, measure quantitative responses of test subjects by changing independent variables of a test system. For wind tunnel tests, the independent variables are model attitude parameters, model control surface parameters and flow field parameters, the forces and moments, pressure distribution, temperature distribution and the like which are required to be quantitatively measured are applied to the model, and the wind tunnel flow field parameters such as pressure, flow velocity, temperature, mach number and the like are directly related to the quantitative reaction accuracy of test objects, so that the accurate determination of the flow field parameters of air flow flowing through a wind tunnel test section is extremely critical.
At present, when wind tunnel tests are carried out, the flow field parameters of the low-speed wind tunnel are generally measured by installing a single pitot tube or double pitot tube device at a test inlet, on one hand, when the model disturbance is large, the total pressure and the static pressure are influenced, the measurement accuracy of the rapid pressure is directly influenced, on the other hand, the pitot tube can generate extra noise and disturbance to a convection field, and meanwhile, the measurement precision of the device is directly influenced by the measurement precision of a sensor.
Therefore, it is needed to provide a low-speed wind tunnel flow field parameter measuring device and method for solving the above technical problems.
Disclosure of Invention
The invention is developed to provide a low-speed wind tunnel flow field parameter measuring device and method which are arranged in a wind tunnel stabilizing section and a contraction section in a distributed manner, so as to realize the problem of accurately measuring the test incoming flow field parameter in the low-speed wind tunnel, and brief summary of the invention is provided below so as to provide a basic understanding of some aspects of the invention. It should be understood that this summary is not an exhaustive overview of the invention. It is not intended to identify key or critical elements of the invention or to delineate the scope of the invention.
The technical scheme of the invention is as follows:
the low-speed wind tunnel flow field parameter measuring device comprises two measuring rakes and a static pressure disc, wherein the two measuring rakes are respectively arranged at two ends of a pressure measuring pipeline;
the structure of the two measuring rakes is the same, the measuring rakes comprise a total pressure probe, a temperature sensor supporting tube, a temperature sensor, an airfoil supporting tube base, a humidity sensor supporting tube and a humidity sensor, the airfoil supporting tube is fixedly arranged on the airfoil supporting tube base, one end of the total pressure probe is fixedly arranged on the airfoil supporting tube base, the other end of the total pressure probe penetrates through the airfoil supporting tube and then is arranged outside one side of the airfoil supporting tube, one end of the temperature sensor supporting tube is fixedly arranged on the airfoil supporting tube base, the other end of the temperature sensor supporting tube penetrates through the airfoil supporting tube and then is arranged outside one side of the airfoil supporting tube, the temperature sensor is arranged in the temperature sensor supporting tube, the measuring ends of the temperature sensor and the total pressure probe are arranged on the same side outside the airfoil supporting tube, and the humidity sensor is fixedly arranged on the airfoil supporting tube base through the humidity sensor supporting tube.
Preferably: and the pressure measuring pipeline is provided with a plurality of differential pressure sensors.
Preferably: the static pressure disk comprises a first static pressure disk, a second static pressure disk, a third static pressure disk and a fourth static pressure disk, a first differential pressure sensor is arranged between the first static pressure disk and a measuring rake at one end of a pressure measuring pipeline, a second differential pressure sensor is arranged between the fourth static pressure disk and a measuring rake at the other end of the pressure measuring pipeline, a third differential pressure sensor is arranged on the pressure measuring pipeline, the first static pressure disk is arranged on the pressure measuring pipeline through the third differential pressure sensor, the second static pressure disk and the third static pressure disk are arranged at the same position of the pressure measuring pipeline, an absolute pressure sensor is arranged at the joint of the second static pressure disk and the third static pressure disk, a fourth differential pressure sensor is arranged between the third static pressure disk and the absolute pressure sensor, and a fifth differential pressure sensor is arranged between the fourth static pressure disk and the absolute pressure sensor.
Preferably: the first static pressure plate, the second static pressure plate, the third static pressure plate and the fourth static pressure plate have the same structure, and the first static pressure plate, the second static pressure plate, the third static pressure plate and the fourth static pressure plate are fixedly arranged on the wall of the wind tunnel shrinkage section through wind tunnel shrinkage section wall mounting seats, and a static pressure hole is formed in the center of the first static pressure plate.
The second scheme and the measuring method of the low-speed wind tunnel flow field parameters are realized based on the first scheme, and the measuring device of the low-speed wind tunnel flow field parameters comprises the following steps:
s1, two measuring rakes are respectively arranged at the horizontal line positions of two side walls of a stabilizing section, and the measuring ends of the temperature sensor and the total pressure probe of the two measuring rakes are arranged at the same side outside the wing-shaped supporting frame;
s2, embedding the wing-shaped support frame base into the wall of the stable section of the wind tunnel to enable the measurement end of the total pressure probe to be parallel to the axis of the wind tunnel, and enabling the wing-shaped support frame base and the wall surface of the wind tunnel to be smooth, excessively and without steps;
s3, the static pressure disc is embedded and mounted on four wall surface horizontal lines at the outlet of the contraction section through screws and is positioned on the same cross section of the wind tunnel, and the connecting part of the static pressure disc is subjected to sealing treatment by adopting a sealing ring, so that the static pressure disc and the wind tunnel wall surface are smooth and excessively without steps; one side of the static pressure disk is a circular plane, and a static pressure hole parallel to the normal direction of the plane of the static pressure disk is designed at the center of the circle;
s4, connecting a static pressure hole on a static pressure plate with a total pressure probe through a pressure measuring pipeline and a pressure difference sensor;
s5, carrying out multi-path block average calculation on data acquired by a plurality of differential pressure sensors and absolute pressure sensors, and acquiring a pressure relation between a wind tunnel center flow field parameter and a total pressure probe and a static pressure disk when a wind tunnel flow field is calibrated, namely a formula (5.1) and a formula (5.2), and deriving a formula (5.3) to a formula (5.7) through the formula (5.1), the formula (5.2) and an equal moisture formula to obtain a test piece incoming flow parameter, namely a low-speed wind tunnel flow field parameter when a wind tunnel test piece is tested, wherein the test piece incoming flow parameter comprises a test piece center total pressure, a test piece center total static pressure difference, a test piece center Mach number, a test piece center speed pressure and a wind tunnel total temperature;formula (5.1)
Wherein:for the total pressure of the center of the test section, < > for>For the total pressure a coefficient is to be determined, < >>For the pressure difference between the total pressure probe and the static pressure plate, +.>Is static pressure on static pressure plate, +.>The fitting times are;
formula (5.2)
Wherein:for the total static pressure difference in the center of the test section, +.>The coefficient to be solved is static pressure;
formula (5.3)
Formula (5.4)
Formula (5.5)
Formula (5.6)
Formula (5.7)
Wherein:for the center Mach number of the test section,/->For test section centre speed pressing +.>Is wind tunnel static temperature>Is the total temperature of wind tunnel>Is the local sound velocity，/>Is air gas constant, +.>Is the specific heat ratio of air, and the air is heated,Vis the center wind speed of the test section.
The invention has the following beneficial effects:
1. the large model and the four static pressure holes under a large angle can more comprehensively represent incoming flows, and the simulation is more reasonable and more real when the incoming flows are disturbed by the model and have non-uniformity;
2. the invention avoids the problem of aerodynamic noise interference existing in the placement of the pitot tube in a high flow velocity region such as an inlet of a test section, and better meets the requirements of an acoustic wind tunnel;
3. according to the invention, all components arranged on the pressure measuring pipeline are mutually connected, so that errors caused by acquisition of a single sensor can be reduced through average calculation, and the mutual monitoring and measurement can be realized, thereby ensuring the reliability of the system;
4. all pressure measurement points and air flow in the wind tunnel form a passage through the pressure sensors, and the pressure sensors are arranged at a plurality of positions of the wind tunnel, so that the flow parameters can be comprehensively represented.
Drawings
FIG. 1 is a perspective view of a low-speed wind tunnel flow field parameter measuring device of the present invention;
FIG. 2 is a diagram showing the cooperative installation of a measuring rake of a low-speed wind tunnel flow field parameter measuring device according to the present invention;
FIG. 3 is a top view of FIG. 2;
FIG. 4 is a cross-sectional view A-A of FIG. 2;
FIG. 5 is a mating installation view of the first stationary platen;
fig. 6 is a right side view of fig. 5.
In the figure: the device comprises a 1-measuring rake, a 2-static plate, a 3-pressure measuring pipeline, a 4-differential pressure sensor, a 5-absolute pressure sensor, an 11-total pressure probe, a 12-temperature sensor supporting tube, a 13-temperature sensor, a 14-airfoil supporting tube, a 15-airfoil supporting tube base, a 16-humidity sensor supporting tube, a 17-humidity sensor, a 21-first static plate, a 22-second static plate, a 23-third static plate, a 24-fourth static plate, a 25-wind tunnel shrinkage section hole wall mounting seat, a 26-wind tunnel shrinkage section hole wall, a 27-static pressure hole, a 41-first differential pressure sensor, a 42-second differential pressure sensor, a 43-third differential pressure sensor, a 44-fourth differential pressure sensor and a 45-fifth differential pressure sensor.
Detailed Description
For the purpose of making the objects, technical solutions and advantages of the present invention more apparent, the present invention is described below by means of specific embodiments shown in the accompanying drawings. It should be understood that the description is only illustrative and is not intended to limit the scope of the invention. In addition, in the following description, descriptions of well-known structures and techniques are omitted so as not to unnecessarily obscure the present invention.
The connection mentioned in the invention is divided into a fixed connection and a detachable connection, wherein the fixed connection is a conventional fixed connection mode such as a non-detachable connection including but not limited to a hemmed connection, a rivet connection, an adhesive connection, a welded connection and the like, the detachable connection is a conventional detachable mode such as a threaded connection, a snap connection, a pin connection, a hinge connection and the like, and when a specific connection mode is not limited explicitly, at least one connection mode can be found in the conventional connection mode by default, so that the function can be realized, and a person skilled in the art can select the device according to needs. For example: the fixed connection is welded connection, and the detachable connection is hinged connection.
The first embodiment is as follows: referring to fig. 1-6, a low-speed wind tunnel flow field parameter measuring device of the present embodiment is described, and includes two measuring rakes 1 and a static pressure disc 2, wherein the two measuring rakes 1 are respectively installed at two ends of a pressure measuring pipeline 3, and the static pressure disc 2 is installed in the middle of the pressure measuring pipeline 3; the pressure measuring pipeline 3 is provided with a plurality of differential pressure sensors 4, namely a first differential pressure sensor 41, a second differential pressure sensor 42, a third differential pressure sensor 43 and a fourth differential pressure sensor 44, the measuring rake 1 is used for measuring the total pressure and the total mild humidity of the airflow in the stable section, and the static pressure of the wall of the shrinkage section is obtained through a loop formed by the static pressure plate 2, the pressure measuring pipeline 3 and the pressure sensor 4;
the static pressure disc 2 comprises a first static pressure disc 21, a second static pressure disc 22, a third static pressure disc 23 and a fourth static pressure disc 24, a first differential pressure sensor 41 is arranged between the first static pressure disc 21 and the measuring rake 1 at one end of the pressure measuring pipeline 3, a second differential pressure sensor 42 is arranged between the fourth static pressure disc 24 and the measuring rake 1 at the other end of the pressure measuring pipeline 3, a third differential pressure sensor 43 is arranged on the pressure measuring pipeline 3, the first static pressure disc 21 is arranged on the pressure measuring pipeline 3 through the third differential pressure sensor 43, the second static pressure disc 22 and the third static pressure disc 23 are arranged at the same position of the pressure measuring pipeline 3, an absolute pressure sensor 5 is arranged at the joint, a fourth differential pressure sensor 44 is arranged between the third static pressure disc 23 and the absolute pressure sensor 5, and a fifth differential pressure sensor 45 is arranged between the fourth static pressure disc 24 and the absolute pressure sensor 5.
The two measuring rakes 1 have the same structure and are arranged on the same horizontal line, the measuring rakes 1 comprise a total pressure probe 11, a temperature sensor supporting tube 12, a temperature sensor 13, an airfoil supporting frame 14, an airfoil supporting frame base 15, a humidity sensor supporting tube 16 and a humidity sensor 17, the airfoil supporting frame base 15 is vertically and fixedly provided with the airfoil supporting frame 14, the airfoil supporting frame base 15 is embedded into the wall of a wind tunnel stabilizing section to enable the total pressure probe to be parallel to the wind tunnel axis, the airfoil supporting frame base 15 and the wind tunnel wall are smooth and excessively without steps, one end of the total pressure probe 11 is fixedly arranged on the airfoil supporting frame base 15, the other end of the total pressure probe 11 passes through the airfoil supporting frame 14 and is arranged outside one side of the airfoil supporting frame, one end of the temperature sensor supporting tube 12 is fixedly arranged on the airfoil supporting frame base 15, the other end of the temperature sensor supporting tube 12 passes through the wing-shaped supporting frame 14 and then is arranged outside one side of the wing-shaped supporting frame, the temperature sensor 13 is arranged in the temperature sensor supporting tube 12, the measuring ends of the temperature sensor 13 and the total pressure probe 11 are arranged on the same side of the wing-shaped supporting frame 14, the humidity sensor 17 is fixedly arranged on the wing-shaped supporting frame base 15 through the humidity sensor supporting tube 16, the measuring harrow 1 is a symmetrical wing shape, the wing-shaped supporting frame 14 is divided into two symmetrical parts according to structural requirements, the two parts are fixedly connected through countersunk screws, so that the installation, wiring and maintenance of the total pressure probe and the total temperature sensor sleeve are facilitated, the wing-shaped supporting frame has good pneumatic appearance, and the front edge and the rear edge of the wing have good rectifying effect.
The static pressure disc 2 comprises a first static pressure disc 21, a second static pressure disc 22, a third static pressure disc 23 and a fourth static pressure disc 24, a first differential pressure sensor 41 is arranged between the first static pressure disc 21 and the measuring rake 1 at one end of the pressure measuring pipeline 3, a second differential pressure sensor 42 is arranged between the fourth static pressure disc 24 and the measuring rake 1 at the other end of the pressure measuring pipeline 3, the first static pressure disc 21 is arranged on the pressure measuring pipeline 3 through the third differential pressure sensor 43, the second static pressure disc 22 and the third static pressure disc 23 are arranged on the same position of the pressure measuring pipeline 3, an absolute pressure sensor 5 is arranged at the joint, a fourth differential pressure sensor 44 is arranged between the third static pressure disc 23 and the absolute pressure sensor 5, and a fifth differential pressure sensor 45 is arranged between the fourth static pressure disc 24 and the absolute pressure sensor 5.
The first static pressure plate 21, the second static pressure plate 22, the third static pressure plate 23 and the fourth static pressure plate 24 have the same structure, and the first static pressure plate 21, the second static pressure plate 22, the third static pressure plate 23 and the fourth static pressure plate 24 are fixedly arranged on a wind tunnel shrinkage section hole wall 26 through a wind tunnel shrinkage section hole wall mounting seat 25, and a static pressure hole 27 is formed in the center of the first static pressure plate 21.
The second embodiment is as follows: the present embodiment will be described with reference to fig. 1 to 6, and based on the first embodiment, a method for measuring a flow field parameter of a low-speed wind tunnel according to the present embodiment includes:
s1, two measuring rakes 1 are respectively arranged at the horizontal line positions of two side walls of a stabilizing section, and the measuring ends of a temperature sensor 13 and a total pressure probe 11 of the two measuring rakes 1 are arranged on the same side outside an airfoil supporting frame 14;
s2, embedding the wing-shaped support frame base 15 into the wall of the stable section of the wind tunnel to enable the measurement end of the total pressure probe 11 to be parallel to the axis of the wind tunnel, and enabling the wing-shaped support frame base 15 and the wall surface of the wind tunnel to be smooth, excessively and free of steps;
s3, arranging the static pressure plate 2 on four wall surface horizontal lines or symmetrical lines at the outlet of the contraction section in an embedded manner through screws, wherein the four wall surface horizontal lines or symmetrical lines are all positioned on the same cross section of the wind tunnel, and sealing the connecting part of the static pressure plate 2 by adopting a sealing ring to keep the static pressure plate and the wind tunnel wall surface smooth and excessively without steps; one side of the static pressure disc 2 is a circular plane, and a static pressure hole 27 parallel to the normal direction of the plane of the static pressure disc is designed at the center of the circle;
s4, a static pressure hole 27 on a static pressure plate is connected with the total pressure probe 11 through a pressure measuring pipeline 3 and a pressure difference sensor 4;
s5, carrying out multi-path block average calculation on data acquired by a plurality of differential pressure sensors 4 and absolute pressure sensors 5, and obtaining pressure relation formulas between a wind tunnel center flow field parameter and a total pressure probe 11 and a static pressure disk 2, namely a formula (5.1) and a formula (5.2), and deriving formulas (5.3) to (5.7) through formulas (5.1), formulas (5.2) and an equal moisture formula to obtain a test piece incoming flow parameter, namely a low-speed wind tunnel parameter, when the wind tunnel belt test piece is tested, wherein the test piece incoming flow parameter comprises a test piece center total pressure, a test piece center total static pressure difference, a test piece center Mach number, a test piece center speed pressure and a wind tunnel total temperature;formula (5.1)
Wherein:for the total pressure of the center of the test section, < > for>For the total pressure a coefficient is to be determined, < >>For the pressure difference between the total pressure probe and the static pressure plate, +.>Is static pressure on static pressure plate, +.>The fitting times are;
formula (5.2)
Wherein:for the total static pressure difference in the center of the test section, +.>The coefficient to be solved is static pressure;
formula (5.3)
Formula (5.4)
Formula (5.5)
Formula (5.6)
Formula (5.7)
Wherein:for the center Mach number of the test section,/->For test section centre speed pressing +.>Is wind tunnel static temperature>Is the total temperature of wind tunnel>Is the local sound velocity,/->Is air gas constant, +.>Is the specific heat ratio of air, and the air is heated,Vis the center wind speed of the test section.
It should be noted that, in the above embodiments, as long as the technical solutions that are not contradictory can be arranged and combined, those skilled in the art can exhaust all the possibilities according to the mathematical knowledge of the arrangement and combination, so the present invention does not describe the technical solutions after the arrangement and combination one by one, but should be understood that the technical solutions after the arrangement and combination have been disclosed by the present invention.
The above description is only of the preferred embodiments of the present invention and is not intended to limit the present invention, but various modifications and variations can be made to the present invention by those skilled in the art. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention should be included in the protection scope of the present invention.
Claims (2)
1. The utility model provides a low-speed wind tunnel flow field parameter measurement device which characterized in that: the device comprises two measuring rakes (1) and a static pressure disc (2), wherein the two measuring rakes (1) are respectively arranged at two ends of a pressure measuring pipeline (3), the static pressure disc (2) is arranged in the middle of the pressure measuring pipeline (3), the measuring rakes (1) are used for measuring total air flow pressure and total mild humidity of a stable section, and static pressure of a wall of a shrinkage section is obtained through a loop consisting of the static pressure disc (2), the pressure measuring pipeline (3) and a pressure difference sensor (4);
the two measuring rakes (1) have the same structure, the measuring rakes (1) comprise a total pressure probe (11), a temperature sensor supporting tube (12), a temperature sensor (13), an airfoil supporting tube (14), an airfoil supporting tube base (15), a humidity sensor supporting tube (16) and a humidity sensor (17), the airfoil supporting tube (14) is fixedly arranged on the airfoil supporting tube base (15), the airfoil supporting tube base (15) is embedded into the tunnel wall of a wind tunnel stabilizing section, the total pressure probe is parallel to the axis of the wind tunnel, the airfoil supporting tube base (15) and the wall surface of the wind tunnel are smooth and excessively have no steps, one end of the total pressure probe (11) is fixedly arranged on the airfoil supporting tube base (15), the other end of the total pressure probe (11) passes through the airfoil supporting tube (14) and then is arranged on one side of the airfoil supporting tube, one end of the temperature sensor supporting tube (12) is fixedly arranged on the airfoil supporting tube base (15), the other end of the temperature sensor supporting tube (12) passes through the airfoil supporting tube (14) and then is arranged on one side of the airfoil supporting tube, the temperature sensor (13) is arranged in the temperature sensor supporting tube (12), the temperature sensor probe (13) and the total pressure probe (11) are arranged on the outer side of the airfoil supporting tube (14) through the airfoil supporting tube (16), the pressure measuring pipeline (3) is provided with a plurality of differential pressure sensors (4), the measuring harrow (1) is a symmetrical wing profile, the wing profile support frame 14 is divided into two symmetrical parts from the wing profile string, and the two parts are fixedly connected through countersunk head screws;
the static pressure disc (2) comprises a first static pressure disc (21), a second static pressure disc (22), a third static pressure disc (23) and a fourth static pressure disc (24), a first differential pressure sensor (41) is arranged between the first static pressure disc (21) and a measuring rake (1) at one end of a pressure measuring pipeline (3), a second differential pressure sensor (42) is arranged between the fourth static pressure disc (24) and the measuring rake (1) at the other end of the pressure measuring pipeline (3), a third differential pressure sensor (43) is arranged on the pressure measuring pipeline (3), the first static pressure disc (21) is installed on the pressure measuring pipeline (3) through the third differential pressure sensor (43), the second static pressure disc (22) and the third static pressure disc (23) are installed at the same position of the pressure measuring pipeline (3), a pressure insulation sensor (5) is arranged at the joint, a fourth differential pressure sensor (44) is arranged between the third static pressure disc (23) and the pressure insulation sensor (5), and a fifth differential pressure sensor (45) is arranged between the fourth static pressure disc (24) and the pressure insulation sensor (5);
the first static pressure plate (21), the second static pressure plate (22), the third static pressure plate (23) and the fourth static pressure plate (24) are identical in structure, and the first static pressure plate (21), the second static pressure plate (22), the third static pressure plate (23) and the fourth static pressure plate (24) are fixedly installed on a wind tunnel shrinkage section hole wall (26) through a wind tunnel shrinkage section hole wall installation seat (25), and a static pressure hole (27) is machined in the center of the first static pressure plate (21).
2. A method for measuring flow field parameters of a low-speed wind tunnel, which is realized based on the flow field parameter measuring device of the low-speed wind tunnel as claimed in claim 1, and is characterized by comprising the following steps:
s1, two measuring rakes (1) are respectively arranged at the horizontal line positions of two side walls of a stabilizing section, and the measuring ends of a temperature sensor (13) and a total pressure probe (11) of the two measuring rakes (1) are arranged on the same side outside an airfoil supporting frame (14);
s2, embedding an airfoil support frame base (15) into the wall of the stable section of the wind tunnel, so that the measuring end of the total pressure probe (11) is parallel to the axis of the wind tunnel, and the airfoil support frame base (15) and the wall surface of the wind tunnel are smooth, excessively and have no steps;
s3, the static pressure disc (2) is embedded and installed on four wall surface horizontal lines at the outlet of the contraction section through screws and is positioned on the same cross section of the wind tunnel, and the connecting part of the static pressure disc (2) is subjected to sealing treatment by adopting a sealing ring, so that the static pressure disc and the wind tunnel wall surface are kept smooth and excessively without steps; one side of the static pressure disc (2) is a circular plane, and a static pressure hole (27) parallel to the normal direction of the plane of the static pressure disc is designed at the center of the circle;
s4, a static pressure hole (27) on a static pressure plate is connected with a total pressure probe (11) through a pressure measuring pipeline (3) and a pressure difference sensor (4);
s5, carrying out multi-path block average calculation on data acquired by a plurality of differential pressure sensors (4) and absolute pressure sensors (5), and acquiring pressure relation formulas between a wind tunnel center flow field parameter and a total pressure probe (11) and a static pressure disc (2), namely a formula (5.1) and a formula (5.2), wherein a formula (5.1), a formula (5.2) and an equal moisture formula are adopted, namely a formula (5.3) to a formula (5.7) are deduced, so that when a wind tunnel belt test piece is obtained, the incoming flow parameter of the test piece, namely a low-speed wind tunnel flow field parameter, specifically comprises the total pressure of the center of a test section, the total static pressure of the center of the test section, the Mach number of the center of the test section, the central speed of the test section and the total temperature of the wind tunnel;
wherein: p (P) ref For the total pressure of the center of the test section, H i To be the coefficient of total pressure, deltaP s P is the pressure difference between the total pressure probe and the static pressure plate ct The static pressure on the static pressure plate is the fitting frequency i;
wherein: ΔP ref G is the total static pressure difference in the center of the test section i The coefficient to be solved is static pressure;
v=m×a formula (5.7): m is Mach number at the center of the test section, Q is the center rapid pressure of the test section, T is the static temperature of the wind tunnel, T 0 The wind tunnel total temperature is a local sound velocity, R is an air-gas constant, gamma is an air specific heat ratio, and V is a test section center wind speed.
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| CN117147092B (en) * | 2023-10-30 | 2024-01-23 | 中国航空工业集团公司沈阳空气动力研究所 | Ultrasonic static pressure probe-based acoustic explosion near-field space pressure measurement device |
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| JP4256900B2 (en) * | 2007-09-20 | 2009-04-22 | 三菱重工業株式会社 | Measuring unit of wind tunnel test apparatus and wind tunnel test apparatus using the same |
| CN105258914B (en) * | 2015-11-13 | 2019-01-08 | 中国空气动力研究与发展中心低速空气动力研究所 | A kind of low-speed wind tunnel flow field test micro-pressure measurement system |
| CN105387992A (en) * | 2015-11-26 | 2016-03-09 | 中国航空工业集团公司哈尔滨空气动力研究所 | Airfoil profile support device and support method |
| CN107356288B (en) * | 2017-06-09 | 2019-12-31 | 同济大学 | Air flow speed and temperature composite measuring device for low-speed flow field |
| CN108088647B (en) * | 2017-12-04 | 2020-03-10 | 中国航空工业集团公司哈尔滨空气动力研究所 | Five-degree-of-freedom boundary layer measuring system for wind tunnel test |
| CN211668740U (en) * | 2020-01-20 | 2020-10-13 | 北京航空航天大学 | Multi-point dynamic full-parameter measuring device for subsonic two-dimensional flow field |
| CN111220348B (en) * | 2020-03-06 | 2024-10-01 | 上海海事大学 | Composite five-hole pressure-temperature probe |
| JP7421769B2 (en) * | 2020-03-19 | 2024-01-25 | 株式会社Subaru | Duct pressure measurement structure and wind tunnel test equipment |
| CN111982457A (en) * | 2020-08-14 | 2020-11-24 | 西安航天动力研究所 | Mach number measuring device under high temperature supersonic flow field environment |
| CN112649172B (en) * | 2020-12-21 | 2022-12-16 | 中国航天空气动力技术研究院 | Static pressure probe and high-enthalpy shock tunnel static pressure measurement method |
| CN113916486B (en) * | 2021-10-11 | 2022-12-30 | 中国航空工业集团公司哈尔滨空气动力研究所 | Low-speed wind tunnel rapid pressure measurement and control method based on multi-parameter pressure regression algorithm |
| CN115326346B (en) * | 2022-10-18 | 2023-01-24 | 中国航空工业集团公司哈尔滨空气动力研究所 | Easily-adjusted convertible side wall structure for closed test section |
| CN218646558U (en) * | 2022-12-20 | 2023-03-17 | 中国空气动力研究与发展中心设备设计与测试技术研究所 | Wind tunnel dynamic pressure measuring device |
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