CN118130036B - Vortex generation and measurement test equipment and test method based on delta wing vortex pair - Google Patents
Vortex generation and measurement test equipment and test method based on delta wing vortex pair Download PDFInfo
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- CN118130036B CN118130036B CN202410545839.7A CN202410545839A CN118130036B CN 118130036 B CN118130036 B CN 118130036B CN 202410545839 A CN202410545839 A CN 202410545839A CN 118130036 B CN118130036 B CN 118130036B
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- 238000005259 measurement Methods 0.000 title claims abstract description 38
- 238000012360 testing method Methods 0.000 title claims abstract description 35
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- 238000006073 displacement reaction Methods 0.000 claims abstract description 20
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- 238000004088 simulation Methods 0.000 claims description 3
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
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Abstract
Vortex flow generation and measurement test equipment and test method based on delta wing vortex pair, and belongs to the technical field of aviation aerodynamic force. The invention solves the problem that the prior art can not provide special rotational flow generation and measurement equipment and test flow standard for the test of the airplane model in the wind tunnel. The technical key points are as follows: the bottom plate is fixed on the bottom wall of the wind tunnel wall, the sliding block is arranged on the bottom plate, the delta wing model is arranged at the top end of the sliding block through an attack angle changing device, and the attack angle changing device is used for adjusting the attack angle of the delta wing model; the electric control displacement platform is arranged on the top wall of the wind tunnel wall, the vertical five-hole probe measuring rake is vertically arranged on the electric control displacement platform, the five-hole probe is arranged on the vertical five-hole probe measuring rake, the pressure measuring hose led out by the five-hole probe is connected with the pressure collecting system arranged outside the wind tunnel, and the pressure collecting system is connected with the computer. The invention provides special equipment and test flow standard for the test of the aircraft model in the wind tunnel.
Description
Technical Field
The invention belongs to the technical field of aviation aerodynamic force, and particularly relates to vortex generation and measurement test equipment and a test method based on delta wing vortex pair.
Background
When the aircraft model is tested in a wind tunnel, the front flow field is basically a uniform flow field, and when the front incoming flow has disturbance, the performance of the aircraft, especially the inlet flow field of an aircraft inlet channel, is influenced, so that the flow field in the whole inlet channel is influenced, the air flow parameters of each section of the inlet channel are unevenly distributed, the flow field of the outlet of the inlet channel is influenced, the performance and the stability of a gas compressor are changed, and the stable operation of an engine is possibly influenced.
When the airflow passes through the delta wing model, symmetrical wingtip vortices are formed at the wingtips of the delta wings. However, in the prior art, a rotational flow generation and measurement test device and a test method based on delta wing vortex pair are lacked, and special equipment and test flow standards cannot be provided for the test of an aircraft model in a wind tunnel.
Disclosure of Invention
The invention aims to provide vortex generation and measurement test equipment and a test method based on delta wing pair vortex, which are used for solving the problem that the prior art cannot provide special vortex generation and measurement equipment and test flow standard for the test of an aircraft model in a wind tunnel.
The technical scheme adopted by the invention is as follows:
Scheme one: the vortex generating and measuring test equipment based on the vortex pair of the delta wing comprises a delta wing model and a supporting system, a variable-distance system and a vortex measuring system, wherein the delta wing model and the supporting system and the vortex measuring system are arranged left and right;
The delta wing model and the supporting system comprise a delta wing model and an attack angle changing device; the variable-distance system comprises a sliding block and a bottom plate; the rotational flow measurement system comprises a five-hole probe, a vertical five-hole probe measurement rake, an electric control displacement table, a pressure acquisition system and a computer;
The base plate is fixed on the bottom wall of the wind tunnel wall, the sliding block is arranged on the base plate, the delta wing model is arranged at the top end of the sliding block through an attack angle changing device, and the attack angle changing device is used for adjusting the attack angle of the delta wing model;
The electric control displacement platform is arranged on the top wall of the wind tunnel wall, the vertical five-hole probe measuring rake is vertically arranged on the electric control displacement platform, the five-hole probe is arranged on the vertical five-hole probe measuring rake, the five-hole probe is arranged towards the incoming flow direction, the pressure measuring hose led out by the five-hole probe is connected with the pressure collecting system arranged outside the wind tunnel, and the pressure collecting system is connected with the computer.
Further: the angle of attack changing device comprises a fixed support rod and a telescopic support rod, wherein the fixed support rod and the telescopic support rod are arranged in parallel front and back, the bottom ends of the fixed support rod and the telescopic support rod are fixedly connected with a sliding block, and the top ends of the fixed support rod and the telescopic support rod are hinged with the delta wing model.
Scheme II: the method is realized by means of the vortex generation and measurement test equipment based on the delta wing vortex, and comprises the following specific steps of:
Step 1: the method comprises the steps of installing a variable-distance system, fixing a bottom plate of the variable-distance system on the bottom wall of a wind tunnel wall, installing a sliding block on the bottom plate, installing a delta wing model on the top end of the sliding block through an attack angle changing device, and adjusting the attack angle of the delta wing model to an initial attack angle set in a test through the attack angle changing device;
Step 2: the method comprises the steps that a five-hole probe is mounted on a vertical five-hole probe measuring rake, the vertical five-hole probe measuring rake is mounted on an electric control displacement table, a pressure measuring hose led out by the five-hole probe is connected with a pressure acquisition system, the pressure acquisition system transmits pressure to a computer, and the surface of a detection end of the five-hole probe is a measuring section;
Step 3: when the test is carried out, after a stable flow field is established in the wind tunnel, the pressure acquisition system starts to acquire the pressure received by the five-hole probe, after the first vertical position pressure data acquisition is completed, the electric control displacement table is used for controlling the vertical five-hole probe measuring rake to carry out transverse movement with a fixed step length, in the process of transverse movement, each step length stays for 3 seconds or 4 seconds, the pressure data of the vertical position when each step length stays is acquired, and after the acquisition is completed, the rotational flow intensity on each measuring section is obtained through a computer;
Step 4: and (3) adjusting the attack angle of the delta wing model through the attack angle changing device, adjusting the distance between the rear edge of the delta wing model and the measurement section through the distance changing system, repeating the step (3) until a vortex flow field of vortex flow intensity required by a test is obtained, recording the attack angle of the delta wing model and the distance between the rear edge and the measurement section, and realizing simulation of vortex flow generation and measurement of given vortex flow intensity.
Compared with the prior art, the invention has the beneficial effects that: the invention is based on symmetrical wingtip vortex generated by a delta wing model in a flow field, and combines a vertical five-hole probe measuring rake under the control of an electric control displacement table to carry out transverse movement of a given step length so as to obtain the rotational flow intensity of the flow field with a measured section. According to the invention, by adjusting the attack angle of the delta wing model and the distance between the rear edge of the model and the measurement section, the downstream rotational flow measurement section of the flow field finally reaches a given rotational flow strength, the attack angle of the delta wing model and the distance between the rear edge of the delta wing model and the measurement section are calibrated, and the delta wing model and the support system are rotational flow generating devices based on delta wing opposite vortex which can generate the given rotational flow strength; the invention provides special equipment and test flow standard for the test of the aircraft model in the wind tunnel.
Drawings
FIG. 1 is a front view of a delta wing vortex-based vortex generation and measurement test apparatus of the present invention;
FIG. 2 is a top view of a delta wing vortex-based vortex generation and measurement test apparatus of the present invention;
FIG. 3 is a schematic view of the delta wing model and variable angle of attack device installation relationship of the present invention.
Specific reference numerals in the drawings are: 1. incoming flows; 2. a wind tunnel wall; 3. a delta wing model; 4. an angle of attack changing device; 5. a slide block; 6. a bottom plate; 7. a five-hole probe; 8. a vertical five-hole probe pressure measuring harrow; 9. an electric control displacement table; 10. fixing the support rod; 11. a telescopic strut.
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 fixed connection and detachable connection, wherein the fixed connection is a conventional fixed connection mode such as folding connection, rivet connection, bonding connection, welding connection and the like, the detachable connection comprises a conventional detachable mode such as bolt connection, buckle connection, pin connection, hinge connection and the like, and when a specific connection mode is not limited, at least one connection mode can be found in the conventional connection mode by default to realize the function, and the person skilled in the art can select the function according to the needs. For example: the fixed connection is welded connection, and the detachable connection is bolted connection.
The present invention will be described in further detail with reference to the accompanying drawings, the following examples being illustrative of the present invention and the present invention is not limited to the following examples.
Example 1: as shown in fig. 1 to 3, the vortex generating and measuring test equipment based on delta wing opposite vortex comprises a delta wing model and a support system, a variable-distance system and a vortex measuring system, wherein the delta wing model and the support system and the vortex measuring system are arranged left and right; the delta wing model and the supporting system comprise a delta wing model 3 and an angle of attack changing device 4; the variable-distance system comprises a sliding block 5 and a bottom plate 6; the rotational flow measurement system comprises a five-hole probe 7, a vertical five-hole probe measurement rake 8, an electric control displacement table 9, a pressure acquisition system and a computer; the base plate 6 is fixed on the bottom wall of the wind tunnel wall 2, the sliding block 5 is arranged on the base plate 6, the delta wing model 3 is arranged at the top end of the sliding block 5 through the angle of attack changing device 4, the angle of attack changing device 4 is used for adjusting the angle of attack of the delta wing model 3, and the distance between the rear edge of the delta wing model 3 and the measurement section of the rotational flow measurement system is adjusted through the mutual sliding between the sliding block 5 and the base plate 6; the electric control displacement table 9 is arranged on the top wall of the wind tunnel wall 2, the vertical five-hole probe measuring rake 8 is vertically arranged on the electric control displacement table 9, the five-hole probe 7 is arranged on the vertical five-hole probe measuring rake 8, the five-hole probe 7 is arranged towards the direction of the incoming flow 1, a pressure measuring hose led out of the five-hole probe 7 is connected with a pressure collecting system arranged outside the wind tunnel, and the pressure collecting system is connected with a computer. The angle of attack changing device 4 comprises a fixed support rod 10 and a telescopic support rod 11, the fixed support rod 10 and the telescopic support rod 11 are arranged in parallel front and back, the bottom ends of the fixed support rod 10 and the telescopic support rod 11 are fixedly connected with the sliding block 5, the top ends of the fixed support rod 10 and the telescopic support rod 11 are hinged with the delta wing model 3, the angle of attack of the delta wing model 3 is changed by changing different lengths of the telescopic support rod 11, and therefore the size of wingtip vortex after airflow passes through the delta wing model 3 is controlled. The five-hole probes 7 are equidistantly arranged on the vertical five-hole probe measuring rake 8. The calibrated five-hole probes are integrated on the five-hole probe measuring rake, and the five-hole probes can be arranged equidistantly according to the rotational flow measurement requirement.
In this embodiment, the delta wing model 3 first determines an initial attack angle in the wind tunnel flow field, when the airflow flows through the delta wing model 3, a symmetrical wingtip vortex is generated, so that a vortex flow field is formed in a downstream flow field, the vortex flow measuring system is installed at a specific downstream position, the electric control displacement table 9 controls the vertical five-hole probe rake 8 to perform transverse movement, synchronous measurement is performed during the transverse movement, and the vortex flow intensity of the vortex flow measuring section can be obtained, and then the intensity of the wingtip vortex on the measuring section is adjusted by adjusting the attack angle of the delta wing model 3 and the distance between the rear edge of the delta wing model 3 and the measuring section, so that the vortex flow fields with different vortex flow intensities are simulated.
Example 2: as shown in fig. 1 to 3, the method for testing the generation and measurement of the vortex based on the delta wing pair vortex is realized by the testing equipment for testing the generation and measurement of the vortex based on the delta wing pair vortex according to the embodiment 1, and specifically comprises the following steps:
step 1: a variable-distance system is installed, a bottom plate 6 of the variable-distance system is fixed on the bottom wall of the wind tunnel wall 2, a sliding block 5 is installed on the bottom plate 6, a delta wing model 3 is installed at the top end of the sliding block 5 through an angle of attack changing device 4, and the angle of attack of the delta wing model 3 is adjusted to an initial angle of attack set in a test through the angle of attack changing device;
Step 2: the five-hole probe 7 is mounted on a vertical five-hole probe measuring rake 8, the vertical five-hole probe measuring rake 8 is mounted on an electric control displacement table 9, a pressure measuring hose led out of the five-hole probe 7 is connected with a pressure acquisition system, the pressure acquisition system transmits pressure to a computer, and the surface of a detection end of the five-hole probe 7 is a measuring section;
Step 3: when the test is carried out, after a stable flow field is established in the wind tunnel, the pressure acquisition system starts to acquire the pressure received by the five-hole probe 7, after the first vertical position pressure data acquisition is completed, the electric control displacement table 9 is used for controlling the vertical five-hole probe measurement rake 8 to carry out transverse movement with fixed step length, in the process of transverse movement, each step length stays for 3 seconds or 4 seconds, the pressure data of the vertical position when each step length stays is acquired, and after the acquisition is completed, the rotational flow intensity on each measurement section is obtained through a computer;
Step 4: and adjusting the attack angle of the delta wing model 3 through the attack angle changing device 4, adjusting the distance between the rear edge of the delta wing model 3 and the measurement section through the distance changing system, repeating the step 3 until a vortex flow field of the swirl intensity required by the test is obtained, recording the attack angle of the delta wing model 3 and the distance between the rear edge and the measurement section, and realizing simulation of vortex flow generation and measurement of the given swirl intensity.
The above embodiments are only illustrative of the present invention and do not limit the scope thereof, and those skilled in the art may also make modifications to parts thereof without departing from the spirit of the invention.
Claims (2)
1. The method is realized by means of a vortex generating and measuring test device based on delta wing vortex, wherein the test device comprises a delta wing model and a support system, a variable-distance system and a vortex measuring system, and the delta wing model and the support system and the vortex measuring system are arranged left and right;
the delta wing model and the supporting system comprise a delta wing model (3) and an attack angle changing device (4); the variable-distance system comprises a sliding block (5) and a bottom plate (6); the rotational flow measurement system comprises a five-hole probe (7), a vertical five-hole probe measurement rake (8), an electric control displacement table (9), a pressure acquisition system and a computer;
The base plate (6) is fixed on the bottom wall of the wind tunnel wall (2), the sliding block (5) is arranged on the base plate (6), the delta wing model (3) is arranged at the top end of the sliding block (5) through the angle of attack changing device (4), and the angle of attack changing device (4) is used for adjusting the angle of attack of the delta wing model (3);
the electric control displacement table (9) is arranged on the top wall of the wind tunnel wall (2), the vertical five-hole probe measuring rake (8) is vertically arranged on the electric control displacement table (9), the five-hole probe (7) is arranged on the vertical five-hole probe measuring rake (8), the five-hole probe (7) is arranged towards the direction of the incoming flow (1), a pressure measuring hose led out of the five-hole probe (7) is connected with a pressure collecting system arranged outside the wind tunnel, and the pressure collecting system is connected with a computer;
The test method is characterized by comprising the following specific steps of:
Step 1: the method comprises the steps of installing a variable-distance system, fixing a bottom plate (6) of the variable-distance system on the bottom wall of a wind tunnel wall (2), installing a sliding block (5) on the bottom plate (6), installing a delta wing model (3) on the top end of the sliding block (5) through an attack angle changing device (4), and adjusting the attack angle of the delta wing model (3) to an initial attack angle set in a test through the attack angle changing device;
Step 2: the five-hole probe (7) is arranged on a vertical five-hole probe measuring rake (8), the vertical five-hole probe measuring rake (8) is arranged on an electric control displacement table (9), a pressure measuring hose led out of the five-hole probe (7) is connected with a pressure collecting system, the pressure collecting system transmits pressure to a computer, and the surface of a detection end of the five-hole probe (7) is a measuring section;
Step 3: when the test is carried out, after a stable flow field is established in the wind tunnel, the pressure acquisition system starts to acquire the pressure received by the five-hole probe (7), after the first vertical position pressure data acquisition is completed, the electric control displacement table (9) is used for controlling the vertical five-hole probe measuring rake (8) to carry out transverse movement with fixed step length, in the process of transverse movement, each step length stays for 3 seconds or 4 seconds, the pressure data of the vertical position when each step length stays is acquired, and after the acquisition is completed, the rotational flow intensity on each measuring section is obtained through a computer;
Step 4: and adjusting the attack angle of the triangular wing model (3) through the attack angle changing device (4), adjusting the distance between the rear edge of the triangular wing model (3) and the measurement section through the variable-distance system, repeating the step (3) until a vortex flow field of the swirl intensity required by the test is obtained, recording the attack angle of the triangular wing model (3) and the distance between the rear edge and the measurement section, and realizing simulation of vortex flow generation and measurement of the given swirl intensity.
2. The vortex generation and measurement test method based on delta wing vortex according to claim 1, wherein the variable attack angle device (4) comprises a fixed support rod (10) and a telescopic support rod (11), the fixed support rod (10) and the telescopic support rod (11) are arranged in parallel front and back, the bottom ends of the fixed support rod (10) and the telescopic support rod (11) are fixedly connected with the sliding block (5), and the top ends of the fixed support rod (10) and the telescopic support rod (11) are hinged with the delta wing model (3).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202410545839.7A CN118130036B (en) | 2024-05-06 | 2024-05-06 | Vortex generation and measurement test equipment and test method based on delta wing vortex pair |
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| CN202410545839.7A CN118130036B (en) | 2024-05-06 | 2024-05-06 | Vortex generation and measurement test equipment and test method based on delta wing vortex pair |
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| CN118130036B true CN118130036B (en) | 2024-07-09 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113295376A (en) * | 2021-05-25 | 2021-08-24 | 南京航空航天大学 | Small wind tunnel experiment system for research of miniature flapping wing aircraft |
| CN116296236A (en) * | 2023-04-25 | 2023-06-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Method and device for measuring vortex of wing tip of aircraft |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE102005038205B4 (en) * | 2005-08-12 | 2012-07-19 | Airbus Operations Gmbh | Wind tunnel with a model arranged therein, in particular a model of an aircraft, for the detection and evaluation of a large number of measured data and methods |
| JP5244773B2 (en) * | 2009-12-10 | 2013-07-24 | 三菱重工業株式会社 | Wing wind tunnel test method |
| DE202012103700U1 (en) * | 2012-09-26 | 2012-10-22 | Ming Lu | Measuring device for measuring the pressure and the velocity of a vortex flow field |
| CN116499695B (en) * | 2023-06-25 | 2023-09-05 | 中国空气动力研究与发展中心低速空气动力研究所 | Airplane wake field wind tunnel measurement device and method |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113295376A (en) * | 2021-05-25 | 2021-08-24 | 南京航空航天大学 | Small wind tunnel experiment system for research of miniature flapping wing aircraft |
| CN116296236A (en) * | 2023-04-25 | 2023-06-23 | 中国空气动力研究与发展中心高速空气动力研究所 | Method and device for measuring vortex of wing tip of aircraft |
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