CN112763179A - Wing type wind tunnel experiment bench - Google Patents
Wing type wind tunnel experiment bench Download PDFInfo
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- CN112763179A CN112763179A CN202011612780.7A CN202011612780A CN112763179A CN 112763179 A CN112763179 A CN 112763179A CN 202011612780 A CN202011612780 A CN 202011612780A CN 112763179 A CN112763179 A CN 112763179A
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- 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
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Abstract
The invention is suitable for the field of wing-shaped wind tunnel test equipment, in particular to a wing-shaped wind tunnel test bench, which comprises: the device comprises an experiment flat plate, a rotating adjusting flat plate is rotationally arranged on the experiment flat plate, and the accurate angle adjustment is completed by utilizing a dial disc arranged on the rotating adjusting flat plate, so that the experiment flat plate is used for wind tunnel tests under different attack angles; the six-component force measuring balance measures force through a plurality of force measuring rods arranged between the experiment flat plate and the six-component force measuring balance, the force measuring rods transmit the force borne by the measured tail fin in the wind tunnel test to the six-component force measuring balance, and the six-component force measuring balance measures the force; the two sides of the tested wing profile are respectively provided with an upper anti-interference wing profile and a lower anti-interference wing profile, and the two sides of the wing profile are used for preventing induced vortexes from being formed on the upper end surface and the lower end surface of the wing profile due to the flow velocity and the pressure difference of the two sides of the wing profile so as to influence the two-dimensional wing profile test result; the upper anti-interference wing profile is fixed through a fixing device on the side face in the incoming flow direction, and is used for reducing the influence of the fixing device on the flow field of the test section.
Description
Technical Field
The invention relates to the field of wing-shaped wind tunnel test equipment, in particular to a wing-shaped wind tunnel test bench.
Background
In the process of designing and developing the negative lift wing profile of an airplane wing or a racing car, a wind tunnel test of the two-dimensional wing profile is required.
When a two-dimensional wing wind tunnel test is carried out, the following problems mainly exist: induced vortexes are formed on two sides of the airfoil profile due to the upper and lower flow velocity and pressure difference of the airfoil profile, so that a two-dimensional airfoil profile test result is influenced; the flow field is unstable, so that the test result is inaccurate; the existing two-dimensional wing wind tunnel test cannot randomly adjust the attack angle of the wing, and the wing is often required to be reinstalled when the attack angle of the wing is required to be changed.
Disclosure of Invention
The invention aims to provide an airfoil wind tunnel experiment bench, which aims to solve the problems in the background technology; in order to achieve the purpose, the invention provides the following technical scheme:
an airfoil wind tunnel experiment bench comprising:
the device comprises an experiment flat plate, a rotating adjusting flat plate is rotationally arranged on the experiment flat plate, and the accurate angle adjustment is completed by utilizing a dial disc arranged on the rotating adjusting flat plate, so that the experiment flat plate is used for wind tunnel tests under different attack angles; the rotary adjusting flat plate is provided with a tested wing profile;
the six-component force measuring balance measures force through a plurality of force measuring rods arranged between the experiment flat plate and the six-component force measuring balance, the force measuring rods transmit the force borne by the measured tail fin in the wind tunnel test to the six-component force measuring balance, and the six-component force measuring balance measures the force;
the upper anti-interference wing section and the lower anti-interference wing section are positioned on two sides of the tested wing section and are used for preventing induced vortexes from being formed on the upper end surface and the lower end surface of the wing section due to the flow velocity and the pressure difference of the two sides of the wing section so as to influence a two-dimensional wing section test result;
the upper anti-interference wing profile is fixed through a fixing device on the side face in the incoming flow direction, and is used for reducing the influence of the fixing device on the flow field of the test section.
The six-component force measuring antenna and the force measuring rod are both arranged below the floor of the wind tunnel test section, and the influence of the single measured wing profile of the test flat plate on the flow field of the wind tunnel test can be reduced.
In the wing wind tunnel experiment bench of the invention: the angle adjusting range of the dial is-20 degrees to 20 degrees, and long scale marks are arranged at intervals of 5 degrees.
In the wing wind tunnel experiment bench of the invention: the two force measuring rods are arranged and are distributed between the experiment flat plate and the six-component force measuring balance in parallel;
two openings are formed in the rotating adjusting plate, the two force measuring rods penetrate through the openings (the force measuring rods realize no allowance and rotate at the same angle), and the two force measuring rods are tightly connected to the lower anti-interference wing profiles.
The force measuring rod penetrates through the opening to be fixedly connected to the lower anti-interference wing section, and the rotation of the rotating adjusting plate and the force measuring rod can be synchronously realized.
Further scheme: the force measuring rod is fixedly connected to the lower anti-interference wing section through a blind hole formed in the lower anti-interference wing section.
Preferably: the depth of the blind hole is 70% -80% of the length of the measured tail wing so as to realize the fastening connection with the force measuring rod and avoid the measurement error caused by the deformation of the force measuring rod to a greater extent.
In the wing wind tunnel experiment bench of the invention: the force measuring rod is arranged on the six-component force measuring balance through the force measuring flat plate;
the lower end of the force measuring rod is fixedly connected with the force measuring flat plate.
Further scheme: the force measuring flat plate is connected with the six-component force measuring balance through a bolt; and the installation positions of the force measuring flat plate and the six-component force measuring balance are horizontal and are used for transmitting force without additional moment.
Preferably: the six-component balance is installed on the supporting base through fastening bolts.
The force measuring rod is a component which transmits the force applied to the measured tail wing in the wind tunnel test to the force measuring flat plate and is measured by the six-component force measuring balance; the lower end of the force measuring rod is fixedly connected with the force measuring flat plate; the tail end of the force measuring rod exceeds a part of the lower end face of the force measuring flat plate but does not contact with the upper end face of the supporting base, so that the force passing through the force measuring rod can be better transmitted to the force measuring flat plate.
The support base is provided with two symmetrical arc-shaped extension holes, and the fixing bolt can realize the fixation of the support base and the floor through the arc-shaped extension holes. The arc-shaped extension holes are arranged in a central symmetry mode, and the centers of the arc-shaped extension holes are consistent with the rotation center of the rotation adjusting flat plate so as to realize concentric rotation. The two arc-shaped extension holes are used for realizing that the rotating angle threshold is larger than or equal to the angle threshold of the dial scales on the rotating adjusting flat plate and the experiment flat plate so as to ensure that the corresponding range of the angle of the dial scales can be adjusted as required.
In the wing wind tunnel experiment bench of the invention: the fixing device is provided with an upper empennage fixing rod and is fixed on the upper anti-interference wing section through the upper empennage fixing rod;
the other end of the upper empennage fixing rod is fixed on the fixing base.
The end surface shapes of the upper anti-interference wing section and the lower anti-interference wing section are the same as those of the wing section to be measured.
Compared with the prior art, the wing-shaped wind tunnel experiment bench provided by the invention comprises: the device comprises an experiment flat plate, a rotating adjusting flat plate is rotationally arranged on the experiment flat plate, and the accurate angle adjustment is completed by utilizing a dial disc arranged on the rotating adjusting flat plate, so that the experiment flat plate is used for wind tunnel tests under different attack angles; the rotary adjusting flat plate is provided with a tested wing profile; the six-component force measuring balance measures force through a plurality of force measuring rods arranged between the experiment flat plate and the six-component force measuring balance, the force measuring rods transmit the force borne by the measured tail fin in the wind tunnel test to the six-component force measuring balance, and the six-component force measuring balance measures the force; the upper anti-interference wing section and the lower anti-interference wing section are positioned on two sides of the tested wing section and are used for preventing induced vortexes from being formed on the upper end surface and the lower end surface of the wing section due to the flow velocity and the pressure difference of the two sides of the wing section so as to influence a two-dimensional wing section test result; the upper anti-interference wing profile is fixed by a fixing device on the side surface in the incoming flow direction and is used for reducing the influence of the fixing device on the flow field of the test section; the six-component force measuring antenna and the force measuring rod are both arranged below the floor of the wind tunnel test section, and the influence of the single measured wing profile of the test flat plate on the flow field of the wind tunnel test can be reduced.
Drawings
FIG. 1 is a schematic structural diagram of an airfoil wind tunnel experiment bench of the present invention.
Fig. 2 is a schematic top view of the experimental panel shown in fig. 1.
In the figure:
11-measured airfoil profile; 12-rotating the adjusting plate; 13-Experimental plate; 14-a force measuring bar; 15-force measuring flat plate; 16-measuring a six-component balance; 17-a support base; 18-a fastening bolt;
21-installing an anti-interference wing profile; 22-lower anti-interference wing section;
31-upper tail fixing rod; 32-fixed base.
Detailed Description
The technical solution of the present invention will be described in further detail with reference to specific embodiments.
As shown in fig. 1-2, in an embodiment of the present invention, an airfoil wind tunnel experiment bench includes: the device comprises an experiment flat plate 13, wherein a rotation adjusting flat plate 12 is additionally arranged on the experiment flat plate 13 in a rotating mode, and the accurate angle adjustment is completed by utilizing a dial disc arranged on the rotation adjusting flat plate 12 and is used for wind tunnel tests under different attack angles; the rotary adjusting flat plate 12 is provided with a tested wing section 11; the six-component force measuring balance 16 is used for measuring force through a plurality of force measuring rods 14 arranged between the experiment flat plate 13 and the six-component force measuring balance 16, the force measuring rods 14 are used for transmitting the force applied to the measured tail fin 11 in the wind tunnel test to the six-component force measuring balance 16, and the force is measured through the six-component force measuring balance 16;
the upper anti-interference wing section 21 and the lower anti-interference wing section 22 are respectively arranged on two sides of the tested wing section 11, and the upper anti-interference wing section 21 and the lower anti-interference wing section 22 are used for preventing induced vortexes from being formed on the upper end surface and the lower end surface of the wing section due to the flow velocity and the pressure difference of the two sides of the wing section 11 to influence the two-dimensional wing section test result; the upper anti-interference airfoil 21 is fixed by a fixing device on the side surface in the incoming flow direction, and is used for reducing the influence of the fixing device on the flow field of the test section.
The six-component balance 16 and the force measuring rod 14 are both arranged below the floor of the wind tunnel test section, and the single tested wing section 11 of the test flat plate 13 can reduce the influence on the flow field of the wind tunnel test.
The experiment flat plate 13 is horizontally fixed on the floor of the wind tunnel test section, the thickness of the experiment flat plate 13 is 10mm, a circular opening is formed in the experiment flat plate 13, and the projection of the tested wing profile 11 in the horizontal direction can be completely covered by the circular opening.
As shown in fig. 1-2, in the embodiment of the present invention, in the airfoil wind tunnel experiment table of the present invention: the angle adjusting range of the dial is-20 degrees to 20 degrees, and long scale marks are arranged at intervals of 5 degrees; the two force measuring rods 14 are arranged and are distributed between the experiment flat plate 13 and the six-component force measuring balance 16 in parallel; two openings are formed in the rotation adjusting plate 12, and the two force measuring rods 14 penetrate through the openings (the force measuring rods 14 realize allowance-free rotation at the same angle) and are fixedly connected to the lower anti-interference wing profile 22. The force measuring rod 14 is fixedly connected to the lower anti-interference wing profile 22 through a blind hole formed in the lower anti-interference wing profile 22; the depth of the blind hole is 70% -80% of the length of the tail extension of the measured empennage, so that the blind hole is fastened with the force measuring rod 14, and the measurement error caused by the deformation of the force measuring rod 14 can be avoided to a large extent.
The centers of the two blind holes are the same as the center of the measured tail wing 11, but the diameter of the blind holes is slightly larger than that of the force measuring rod 14, so that the influence of the stress of the lower anti-interference wing profile 22 on the measured wing profile 11 is avoided.
The force measuring rod 14 penetrates through the lower anti-interference wing profile 22 and is fixedly connected with the lower anti-interference wing profile 22 through an opening, so that synchronous rotation with the rotation adjusting plate 12 and the force measuring rod 14 can be realized.
The scale regulating pointer of the rotary regulating flat plate 12 is connected with the center of the two force measuring rods 14, namely the 0-degree attack angle direction of the measured airfoil profile, so as to ensure that the rotary scale angle is the variation of the attack angle. The measuring center of rotation of the six-component balance 16 is matched to the center of rotation of the two force measuring bars 14 on the force measuring plate 15, so that accurate measurement can be realized.
As shown in fig. 1 and 2, in the embodiment of the present invention, the force measuring bar 14 is arranged on the six-component balance 16 through the force measuring plate 15; the lower end of the force measuring rod 14 is fixedly connected with the force measuring flat plate 15; the force measuring flat plate 15 is connected with the six-component force measuring balance 16 through a bolt; the mounting positions of the force measuring flat plate 15 and the six-component force measuring balance 16 are horizontal and are used for transmitting force without additional moment; the six-component force measuring balance 16 is mounted on a support base 17 by fastening bolts 18.
The force measuring rod 14 is a component which transmits the force applied to the measured tail wing 11 in the wind tunnel test to the force measuring flat plate 15 and measures the force through the six-component force measuring balance 16; the lower end of the force measuring rod 14 is fixedly connected with the force measuring flat plate 15; the end of the force measuring bar 14 exceeds a part of the lower end surface of the force measuring plate 15 but does not contact the upper end surface of the supporting base 17, so that the force passing through the force measuring bar 14 can be better transmitted to the force measuring plate 15.
Two symmetrical arc-shaped extension holes are formed in the supporting base 17, and the fixing bolt 18 can fix the supporting base 17 and the floor through the arc-shaped extension holes. The arc-shaped extension holes are arranged in a central symmetry mode, and the centers of the arc-shaped extension holes are consistent with the rotation center of the rotation adjusting flat plate so as to realize concentric rotation. The two arc-shaped extension holes are required to realize that the rotation angle threshold is larger than or equal to the angle threshold of the dial scales on the rotation adjusting flat plate 12 and the experiment flat plate 13 so as to ensure that the corresponding range of the angle of the dial scales can be adjusted as required.
The fixing device is provided with an upper empennage fixing rod 31 and is fixed on the upper anti-interference wing section 21 through the upper empennage fixing rod 31; the other end of the upper tail fixing rod 31 is fixed on a fixing base 32. The end surface shapes of the upper anti-interference wing profile 21 and the lower anti-interference wing profile 22 are the same as those of the wing profile to be measured.
The tail end of the upper empennage fixing rod 31 is vertically arranged and is vertical to the end surface of the upper anti-interference wing section 21; the fixing lever 31 is smoothed.
During testing, because the two sides of the tested tail wing 11 can generate speed and pressure difference, airflow at a high pressure part can be curled to a low pressure part, so that induced vortexes are generated at the two sides of the wing profile, and the test result can be influenced by the generation of the induced vortexes, an anti-interference tail wing 21 and a lower anti-interference tail wing 22 are required to be added to the two ends of the tested tail wing 11 to prevent the airflow from being curled; meanwhile, the lower anti-interference tail 22 is beneficial to enhancing the longitudinal rigidity of the test bench, and the sufficient rigidity ensures that wind vibration cannot occur during bench test so as to avoid the influence of the wind vibration on a flow field and a test result.
In addition, because the air flow can develop and generate boundary layers with certain thickness on the two end surfaces of the measured wing profile 11, the thickness of the boundary layers is increased along with the increase of the distance between the end surfaces of the wing profile and the end surfaces of the upper anti-interference wing profile and the lower anti-interference wing profile, and the flow velocity in the thickness of the boundary layers is unstable; preferably, the distance between the end surfaces of the tested wing profile 11, the upper anti-interference wing profile 21 and the lower anti-interference wing profile 22 is 2mm-3 mm.
The invention relates to a wing-shaped wind tunnel experiment bench, which comprises: the device comprises an experiment flat plate 13, wherein a rotation adjusting flat plate 12 is additionally arranged on the experiment flat plate 13 in a rotating mode, and the accurate angle adjustment is completed by utilizing a dial disc arranged on the rotation adjusting flat plate 12 and is used for wind tunnel tests under different attack angles; the rotary adjusting flat plate 12 is provided with a tested wing section 11; the six-component force measuring balance 16 is used for measuring force through a plurality of force measuring rods 14 arranged between the experiment flat plate 13 and the six-component force measuring balance 16, the force measuring rods 14 are used for transmitting the force applied to the measured tail fin 11 in the wind tunnel test to the six-component force measuring balance 16, and the force is measured through the six-component force measuring balance 16; the upper anti-interference wing section 21 and the lower anti-interference wing section 22 are respectively arranged on two sides of the tested wing section 11, and the upper anti-interference wing section 21 and the lower anti-interference wing section 22 are used for preventing induced vortexes from being formed on the upper end surface and the lower end surface of the wing section due to the flow velocity and the pressure difference of the two sides of the wing section 11 to influence the two-dimensional wing section test result; the upper anti-interference wing section 21 is fixed by a fixing device on the side surface in the incoming flow direction, and is used for reducing the influence of the fixing device on the flow field of the test section; the six-component balance 16 and the force measuring rod 14 are both arranged below the floor of the wind tunnel test section, and the single tested wing section 11 of the test flat plate 13 can reduce the influence on the flow field of the wind tunnel test.
In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
While the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art.
Claims (10)
1. A wing-shaped wind tunnel experiment bench is characterized in that,
the method comprises the following steps:
the device comprises an experiment flat plate, a rotating adjusting flat plate is rotationally arranged on the experiment flat plate, and the accurate angle adjustment is completed by utilizing a dial disc arranged on the rotating adjusting flat plate, so that the experiment flat plate is used for wind tunnel tests under different attack angles; the rotary adjusting flat plate is provided with a tested wing profile;
the six-component force measuring balance measures force through a plurality of force measuring rods arranged between the experiment flat plate and the six-component force measuring balance, the force measuring rods transmit the force borne by the measured tail fin in the wind tunnel test to the six-component force measuring balance, and the six-component force measuring balance measures the force;
the upper anti-interference wing section and the lower anti-interference wing section are positioned on two sides of the tested wing section and are used for preventing induced vortexes from being formed on the upper end surface and the lower end surface of the wing section due to the flow velocity and the pressure difference of the two sides of the wing section so as to influence a two-dimensional wing section test result;
the upper anti-interference wing profile is fixed through a fixing device on the side face in the incoming flow direction, and is used for reducing the influence of the fixing device on the flow field of the test section.
2. The wing wind tunnel experiment bench according to claim 1, wherein the angle adjustment range of the dial is-20 degrees to 20 degrees, and long scale marks are arranged every 5 degrees.
3. The airfoil wind tunnel experiment bench according to claim 1,
the two force measuring rods are arranged and are distributed between the experiment flat plate and the six-component force measuring balance in parallel;
two openings are formed in the rotating adjusting plate, the two force measuring rods penetrate through the openings, and the two force measuring rods are fixedly connected to the lower anti-interference wing section.
4. The wing type wind tunnel experiment bench according to claim 3, wherein the force measuring rod is fastened to the lower anti-interference wing type through a blind hole formed in the lower anti-interference wing type.
5. The airfoil wind tunnel experiment bench according to claim 4, wherein the depth of the blind hole is 70% -80% of the extended length of the measured tail wing.
6. The airfoil wind tunnel experiment bench according to claim 1,
the force measuring rod is arranged on the six-component force measuring balance through the force measuring flat plate;
the lower end of the force measuring rod is fixedly connected with the force measuring flat plate.
7. The wing wind tunnel experiment bench according to claim 6, wherein the force measuring flat plate is connected with the six-component force measuring balance through a bolt; and the installation positions of the force measuring flat plate and the six-component force measuring balance are horizontal and are used for transmitting force without additional moment.
8. The wing wind tunnel experiment bench according to claim 7, wherein the six-component force measuring balance is mounted on the support base through fastening bolts.
9. The airfoil wind tunnel experiment bench according to claim 1,
the fixing device is provided with an upper empennage fixing rod and is fixed on the upper anti-interference wing section through the upper empennage fixing rod;
the other end of the upper empennage fixing rod is fixed on the fixing base.
10. An aerofoil wind tunnel experiment bench according to any one of claims 1-9, wherein the end surfaces of the upper anti-interference aerofoil and the lower anti-interference aerofoil are the same as the tested aerofoil in shape.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011612780.7A CN112763179A (en) | 2020-12-30 | 2020-12-30 | Wing type wind tunnel experiment bench |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202011612780.7A CN112763179A (en) | 2020-12-30 | 2020-12-30 | Wing type wind tunnel experiment bench |
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| CN112763179A true CN112763179A (en) | 2021-05-07 |
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| CN202011612780.7A Pending CN112763179A (en) | 2020-12-30 | 2020-12-30 | Wing type wind tunnel experiment bench |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112964452A (en) * | 2021-02-08 | 2021-06-15 | 中国科学院力学研究所 | Variable-attack-angle hydrofoil experiment model for cutting free surface |
| CN113916493A (en) * | 2021-09-26 | 2022-01-11 | 南京航空航天大学 | Device and method for measuring specific area flow field and global flow field of airfoil under variable attack angle |
| CN115420457A (en) * | 2022-08-22 | 2022-12-02 | 北京航空航天大学 | Adjustable fixing device of wing angle of attack based on wind tunnel test |
| CN115597823A (en) * | 2022-09-08 | 2023-01-13 | 成都流体动力创新中心（Cn） | Open wind tunnel unmanned aerial vehicle wing type aerodynamic force measurement system and method |
| CN116380398A (en) * | 2023-06-06 | 2023-07-04 | 成都流体动力创新中心 | Fixed-wing unmanned plane side wind effect aerodynamic wind tunnel test device and method thereof |
| CN115420457B (en) * | 2022-08-22 | 2024-06-07 | 北京航空航天大学 | Wing attack angle adjustable fixing device based on wind tunnel test |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112964452A (en) * | 2021-02-08 | 2021-06-15 | 中国科学院力学研究所 | Variable-attack-angle hydrofoil experiment model for cutting free surface |
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| CN113916493A (en) * | 2021-09-26 | 2022-01-11 | 南京航空航天大学 | Device and method for measuring specific area flow field and global flow field of airfoil under variable attack angle |
| CN113916493B (en) * | 2021-09-26 | 2022-09-20 | 南京航空航天大学 | Device and method for measuring specific area flow field and global flow field of airfoil under variable attack angle |
| CN115420457A (en) * | 2022-08-22 | 2022-12-02 | 北京航空航天大学 | Adjustable fixing device of wing angle of attack based on wind tunnel test |
| CN115420457B (en) * | 2022-08-22 | 2024-06-07 | 北京航空航天大学 | Wing attack angle adjustable fixing device based on wind tunnel test |
| CN115597823A (en) * | 2022-09-08 | 2023-01-13 | 成都流体动力创新中心（Cn） | Open wind tunnel unmanned aerial vehicle wing type aerodynamic force measurement system and method |
| CN116380398A (en) * | 2023-06-06 | 2023-07-04 | 成都流体动力创新中心 | Fixed-wing unmanned plane side wind effect aerodynamic wind tunnel test device and method thereof |
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