CN109540453B - Wind tunnel test bench of two-dimensional wing section - Google Patents
Wind tunnel test bench of two-dimensional wing section Download PDFInfo
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- CN109540453B CN109540453B CN201811416765.8A CN201811416765A CN109540453B CN 109540453 B CN109540453 B CN 109540453B CN 201811416765 A CN201811416765 A CN 201811416765A CN 109540453 B CN109540453 B CN 109540453B
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- 238000012360 testing method Methods 0.000 title claims abstract description 69
- 238000005192 partition Methods 0.000 claims abstract description 58
- 230000007704 transition Effects 0.000 claims abstract description 9
- 125000006850 spacer group Chemical group 0.000 claims 1
- 238000002474 experimental method Methods 0.000 abstract description 2
- 239000010410 layer Substances 0.000 description 10
- 238000000926 separation method Methods 0.000 description 4
- 230000009286 beneficial effect Effects 0.000 description 2
- 238000009434 installation Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
Classifications
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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
Abstract
The invention discloses a two-dimensional wing-shaped wind tunnel test bed, which comprises: the base is horizontally and fixedly arranged on the floor of the wind tunnel test section and comprises a base main body and two slopes; the two slopes are respectively arranged at two longitudinal ends of the base main body, and the base main body forms transition with the floor through the slopes; the two partition plates are vertically and oppositely arranged on the base main body, and curved surface transition is arranged between the air inlet end of each partition plate and the inner side surface; the cover plate is horizontally arranged on the top of the partition plate; one end of the lever balance rotatably penetrates through one baffle plate, and the wing section is connected to the lever balance between the two baffle plates; the angle adjusting mechanism is fixedly arranged on the outer side of the partition plate, and is detachably connected to the other end of the rod balance and used for adjusting the attack angle of the wing profile; a wind speed sensor disposed between the two diaphragms. The two-dimensional wing type wind tunnel test bed provided by the invention can ensure that a two-dimensional wing type experiment can be accurately carried out in a wind tunnel.
Description
Technical Field
The invention belongs to the technical field of wing type wind tunnel tests, and particularly relates to a two-dimensional wing type wind tunnel test bed.
Background
In the process of designing and developing the wing of an airplane or racing car negative lift wing, a wind tunnel test of a two-dimensional wing is required. When two-dimensional airfoil wind tunnel test is performed, the following problems mainly exist: induced vortex is formed on two sides of the wing profile due to the up-down flow velocity and pressure difference of the wing profile, so that the two-dimensional wing profile test result is affected; the flow field is unstable, resulting in inaccurate test results. In addition, the existing two-dimensional airfoil wind tunnel test cannot adjust the attack angle of the airfoil at will, and when the attack angle of the airfoil needs to be changed, the airfoil is often required to be reinstalled.
Disclosure of Invention
The invention aims to provide a wind tunnel test bench for a two-dimensional airfoil, which is characterized in that a baffle plate is arranged, a cover plate is arranged at the top of the baffle plate, curved surface transition is arranged between the air inlet end and the inner side surface of the baffle plate, a raised bottom plate is arranged, slopes are arranged at the two ends of the bottom plate, and a flow field area where the airfoil is located is formed by enclosing, so that the accuracy of a two-dimensional airfoil test result is improved; and the airfoil attack angle can be arbitrarily changed in the test process, so that the test flow is simplified.
The second purpose of the invention is to ensure the uniform and stable flow velocity at the inlet of the test bed after the wing profile is installed by setting the distance between the air inlet end of the partition plate and the windward end of the wing profile and the distance between the two sides of the wing profile, eliminate the influence of induced vortex at the two sides of the wing profile and the boundary layer of the partition plate, and further ensure the accuracy of the test result.
The technical scheme provided by the invention is as follows:
a two-dimensional airfoil wind tunnel test rig comprising:
the base is horizontally and fixedly arranged on the floor of the wind tunnel test section and comprises a base main body and two slopes;
the two slopes are respectively arranged at two longitudinal ends of the base main body, and the base main body forms transition with the floor through the slopes;
the two partition plates are vertically and oppositely arranged on the base main body along the longitudinal direction of the base main body, and curved surface transition is arranged between the air inlet end and the inner side surface of each partition plate;
the cover plate is horizontally arranged on the top of the partition plate;
one end of the lever balance rotatably penetrates through one baffle plate, and the wing profile is connected to the lever balance between the two baffle plates;
the angle adjusting mechanism is fixedly arranged on the outer side of the partition plate, and is detachably connected to the other end of the rod balance and used for adjusting the attack angle of the wing section;
a wind speed sensor disposed between the two separators.
Preferably, the angle adjusting mechanism comprises an index plate and a three-jaw chuck;
the dividing disc is connected with the three-jaw chuck into a whole, and the rod balance is clamped through the three-jaw chuck.
Preferably, the lever balance is disposed in a horizontal direction.
Preferably, the included angle between the slope and the floor is 8-10 degrees.
Preferably, inclined strut brackets are symmetrically arranged on two sides of the partition plate.
Preferably, the contour line of the projection of the curved surface in the horizontal direction sequentially comprises a first arc and a second arc which are tangent from the end part of the baffle plate to the inner side.
Preferably, the thickness of the separator is 16mm; the curvature radius of the first arc is 10mm, and the corresponding central angle is 30-60 degrees; and two ends of the second circular arc are tangent to the first circular arc and the inner side surface of the partition plate respectively.
Preferably, the distance between the two sides of the airfoil and the two separators is:
wherein C is f The surface friction coefficient is V, incoming wind speed is rho, air density is rho, and mu is a gas viscosity coefficient; c (C) f From the formulaDetermining; in the middle ofX is the distance between the windward end of the airfoil and the edge of the air inlet end of the baffle plate and Re when the maximum attack angle is used for test xtr Is the flow direction reynolds number at the occurrence of turbulent spots.
Preferably, when the maximum attack angle is used for the test, the distance between the windward end of the airfoil and the edge of the air inlet end of the partition plate is as follows:
X＝0.0001L 3 -0.075L 2 +16.952L-541.65；
where L is the height of the projection of the airfoil in the vertical direction at the maximum angle of attack.
The beneficial effects of the invention are as follows:
(1) According to the wind tunnel test stand for the two-dimensional wing profile, provided by the invention, the partition plates are arranged at the two sides of the wing profile, so that the influence of induced vortex formed at the two sides of the wing profile due to the up-down flow velocity and pressure difference of the wing profile on the two-dimensional wing profile test result can be prevented.
(2) The raised floor and the front and rear slopes are arranged, so that the stability of a flow field between the partition boards can be ensured, and meanwhile, the influence of a ground incoming flow boundary layer is eliminated.
(3) And inclined strut brackets are arranged on two sides of the partition plate, so that the test bed has enough strength and rigidity, and wind vibration of the partition plate and the test bed on two sides of the wing profile is eliminated.
(4) The angle of attack of the airfoil can be adjusted and the test can be performed at any angle of attack.
(5) By setting the relative distance between the windward end of the wing profile and the air inlet end of the partition board, the flow velocity of the flow field at the inlet can be ensured to be uniform and stable under the interference of the wing profile to the uniform flow field between the partition boards, and meanwhile, the thickness delta of the boundary layer of the partition board (namely the clearance between the wing profile and the partition board) is ensured to be minimized, so that the accuracy of a test result is further ensured.
(6) The wind speed sensor is arranged between the partition boards, so that the actual wind speed between the partition boards can be obtained.
(7) The air inlet end of the baffle plate is provided with a curved surface transition (cape), so that the influence on experimental results caused by separation of the flow field at the position is avoided.
Drawings
FIG. 1 is a schematic view of the overall structure of a two-dimensional airfoil wind tunnel test stand according to the present invention.
FIG. 2 is a front view of a wind tunnel test stand of a two-dimensional airfoil according to the present invention.
Fig. 3 is an enlarged view at a in fig. 2.
FIG. 4 is a schematic view of the structure of the partition, the base and the cover according to the present invention.
Fig. 5 is a schematic view of the projection of the cape in the horizontal direction.
Detailed Description
The present invention is described in further detail below with reference to the drawings to enable those skilled in the art to practice the invention by referring to the description.
As shown in fig. 1-5, the present invention provides a two-dimensional airfoil wind tunnel test stand comprising: base 110, two baffles 121 and 122, cover 130, diagonal brace bracket 140, bar balance 150, angle adjustment structure 160 and wind speed sensor 170.
The base 110 is horizontally and fixedly arranged on the floor of the wind tunnel test section, and the base 110 comprises a base main body and two slopes 111 arranged at two longitudinal ends of the base main body; the upper surface of the base body is higher than the floor, and the base body forms transition with the floor through a slope 111; the boundaries of the two ends of the base body are flush with the boundaries of the partition boards on the same side of the base body. The slope 111 has an angle with the floor, preferably the angle is set to 8-10 degrees.
The two baffles 121 and 122 are vertically opposite to each other on the upper side of the base body along the longitudinal direction of the base body, and shawl 121a and 122a are respectively arranged at the air inlet ends of the baffles 121 and 122 in order to avoid that the flow field quality between the baffles is affected due to the larger separation of the air flow at the inlet; wherein, the shawl 121a and the shawl 122a are smooth curved surfaces (i.e. the end surface of the air inlet end of the partition board and the inner side surface of the partition board are transited by curved surfaces), and the shawl 121a and the shawl 122a on the two partition boards 121 and 122 are symmetrical.
As shown in fig. 5, taking the shawl 122a as an example, in the present embodiment, a contour line of a projection of the shawl 122a in the horizontal direction includes a first arc 122aa and a second arc 122ab tangent to each other sequentially from a windward end of the partition plate to the inside. Preferably, the thickness of the partition plate is 16mm, the curvature radius of the first circular arc 122aa is 10mm, the corresponding central angle alpha is 30-60 degrees, and two ends of the second circular arc 121ab are respectively tangent with the first circular arc 122a and the inner side surface of the partition plate 122; to further ensure the stability of the air flow entering between the baffles.
The cover plate 130 is horizontally fixedly disposed on top of the two partitions 121 and 122. The outer sides of the two partitions 121 and 122 are symmetrically provided with diagonal bracing brackets 140, and the two partitions are fixedly connected to the diagonal bracing brackets 140.
The bar balance 150 is horizontally disposed with one end rotatably passing through the diaphragm 121 and extending between the diaphragm 121 and the diaphragm 122. The airfoil 200 is disposed between the diaphragm 121 and the diaphragm 122 and is connected to the lever balance 150.
The angle adjusting mechanism 160 is fixedly installed on the bracket 141 at the outer side of the partition 121, and the angle adjusting mechanism 160 is detachably connected to the other end of the bar balance 150, for adjusting the attack angle of the wing profile 200 and clamping the locking bar balance 150. Wherein the bracket 141 is fixedly connected with the diagonal brace bracket 140.
In this embodiment, the angle adjustment mechanism 160 includes an index plate 161 and a three-jaw chuck 162; the index plate 161 is integrally connected to the three-jaw chuck 162, and clamps the lever balance by the three-jaw chuck 162.
A wind speed sensor 170 fixedly disposed between the two diaphragms and located at the lower side of the airfoil 200 for measuring a real-time wind speed between the two diaphragms. The wind speed sensor 170 adopts a pitot tube, the lower end of the pitot tube is fixedly arranged on the base body, the upper end of the pitot tube is lower than the wing section 200 and is positioned on the middle symmetrical plane of the two partition boards, and preferably, the distance between the installation position of the wind speed sensor 170 and the air inlet end of the partition boards is set to be 45-100mm.
During the test, the speed and the pressure difference can be generated from top to bottom of the wing profile, the air flow at the high pressure part can be overturned to the low pressure part, so that induced vortex is generated at two sides of the wing profile, the generation of the induced vortex can influence the test result, and two baffle plates are additionally arranged at two sides of the test bed to block the air flow from overturned, and the baffle plates are fixed on the diagonal bracing support. Meanwhile, the partition board is beneficial to enhancing the longitudinal rigidity of the test bench and plays a role of longitudinal diagonal bracing; the transverse diagonal bracing support strengthens the transverse rigidity of the experimental bench, and the sufficient longitudinal and transverse rigidity ensures that wind vibration cannot occur during bench test so as to avoid the influence of wind vibration on a flow field and test results.
According to the test bed provided by the invention, the upper surface of the base 110 is higher than the floor, and the two ends of the base 110 are provided with the slopes 111. The purpose of raising the upper surface of the base 110 is to eliminate the ground boundary layer, and providing the slopes 111 at both ends of the base 110 can prevent the air flow from being separated at the bottom of the test stand. Tests prove that the flow field at the lower part of the inlet is more stable when the slope exists than when the slope exists under all wind speeds by comparing the flow field conditions of the slope exists or not; when no slope exists, two larger separation areas exist at the bottom of the test bed, the bottom flow field is unstable, and the base surface layer is thick. The front and rear separation areas are eliminated after the slope is added, so that the flow field is more stable, and the slope is connected with the upper surface of the base, so that the boundary layer of the base becomes thinner.
The cover plate is arranged on the upper side of the partition plate, so that the flow field at the upper half part between the two partition plates is isolated from the flow field outside the cover plate, and the influence of the flow field outside the cover plate on the flow field at the upper part of the partition plate is reduced. Tests prove that the flow field is easier to stabilize when the cover plate is added than when the cover plate is not added.
Because the test bed can have weak influence on the air flow speed among the baffles, the air flow speed among the baffles can have small deviation from the air tunnel outlet flow speed. For example, when the wind tunnel airflow velocity is set to 25m/s, the airflow velocity between the baffles is stabilized at 26m/s without the wing profile, so that the wind speed sensor 170 is required to collect the real-time wind speed between the baffles during the test.
In addition, as the airflow develops on both baffles to create a boundary layer of a thickness that increases with increasing distance from the windward edge of the airfoil to the air intake edge of the baffle, the flow velocity is unstable within the boundary layer thickness. As shown in fig. 3, since a boundary layer of a certain thickness is already formed on the partition plate corresponding to the position of the airfoil, the two sides of the airfoil should maintain a certain gap delta with the partition plate and cannot contact with the partition plate.
According to the invention, the relative distance between the windward end of the wing profile and the air inlet end of the partition plate and the gap between the wing profile and the partition plate are determined and set according to the wing profile size, so that the uniform and stable flow velocity at the inlet of the test bed after the wing profile is installed is ensured, and the influence of the boundary layer of the partition plate on experiments is avoided. During the test, the flow field is not uniform and stable due to the influence of the wing profile between the partition plates on the flow field, but the distance between the windward end of the wing profile and the edge of the air inlet end of the partition plate is selected to ensure that the flow velocity is uniform and stable at the inlet, the distance is too small to ensure the flow velocity at the inlet, and the thicker the distance is, the larger the boundary layer is developed, the larger the influence on the test is, so that the value of the distance between the windward end of the wing profile and the edge of the air inlet end of the partition plate is, and the minimum value is taken on the premise of ensuring the flow velocity at the inlet.
In the present embodiment, empirically, the distances between the two ends of the airfoil and the two separators are set to be:
wherein C is f The surface friction coefficient is V, incoming wind speed is rho, air density is rho, and mu is a gas viscosity coefficient; c (C) f From the formulaDetermining; in the middle ofX is the distance between the windward end of the wing section and the edge of the air inlet end of the baffle plate when the test is carried out by using the set maximum attack angle, re xtr Is the flow direction reynolds number at the occurrence of turbulent spots.
As a further preferred aspect, when the test is performed using the maximum attack angle, the distance between the windward end of the airfoil and the edge of the air inlet end of the partition plate is set to be:
X＝0.0001L 3 -0.075L 2 +16.952L-541.65；
wherein L is the projected height of the airfoil in the vertical direction at a set maximum angle of attack.
For example, during the test, the maximum attack angle of the airfoil is set to be 30 degrees, the height of the projection of the airfoil in the vertical direction is taken by L when the attack angle is 30 degrees, and when the test is carried out by changing to other attack angles (such as 0 degree), the installation position of the airfoil is not required to be changed.
Through the arrangement, the flow velocity at the inlet of the test bed after the wing profile is installed can be effectively ensured to be uniform and stable.
When the test is carried out, the test bench is integrally hoisted on the wind tunnel test section, the base 110 is connected with the floor of the wind tunnel test section through bolts, and the air flow inlet is shown by an arrow in FIG. 1. The wing profile 200 is connected with the lever balance 150, the three-grip chuck 162 clamps the lever balance, and the base of the index plate 161 is fixedly connected with the bracket 141 through bolts.
The three-grabbing chuck 162 and the index plate 161 are integrated, the index head of the index plate 161 is adjusted to rotate to drive the three-grabbing chuck 162 to rotate together, and the three-grabbing chuck clamps the lever balance 150, so that the lever balance 150 drives the wing profile to rotate along with the index plate 161, and the index plate is locked by the handle through the index plate 161 after the wing profile rotates to a required angle. The airfoil angle of attack can be adjusted by rotating the indexing disk 161 and clamping the lock at any angle of attack for testing. After the three-grab chuck 162 clamps the lever balance 150, the lever balance (force sensor) 150 is connected with the wing profile 200 to form a cantilever beam structure, and the force and moment applied to the wing profile can be measured through the lever balance 150 and a testing device connected with the lever balance 150.
Although embodiments of the present invention have been disclosed above, it is not limited to the details and embodiments shown and described, it is well suited to various fields of use for which the invention would be readily apparent to those skilled in the art, and accordingly, the invention is not limited to the specific details and illustrations shown and described herein, without departing from the general concepts defined in the claims and their equivalents.
Claims (8)
1. A two-dimensional airfoil wind tunnel test stand, comprising:
the base is horizontally and fixedly arranged on the floor of the wind tunnel test section and comprises a base main body and two slopes;
the two slopes are respectively arranged at two longitudinal ends of the base main body, and the base main body forms transition with the floor through the slopes;
the two partition plates are vertically and oppositely arranged on the base main body along the longitudinal direction of the base main body, and curved surface transition is arranged between the air inlet end and the inner side surface of each partition plate;
the cover plate is horizontally arranged on the top of the partition plate;
one end of the lever balance rotatably penetrates through one baffle plate, and the wing profile is connected to the lever balance between the two baffle plates;
the angle adjusting mechanism is fixedly arranged on the outer side of the partition plate, and is detachably connected to the other end of the rod balance and used for adjusting the attack angle of the wing section;
a wind speed sensor disposed between the two separators; the wind speed sensor adopts a pitot tube;
the distance between the two sides of the airfoil and the two clapboards is as follows:
wherein C is f The surface friction coefficient is V, incoming wind speed is rho, air density is rho, and mu is a gas viscosity coefficient; c (C) f From the formulaDetermining; in the middle ofX is the distance between the windward end of the airfoil and the edge of the air inlet end of the baffle plate and Re when the maximum attack angle is used for test xtr Is the flow direction reynolds number at the occurrence of turbulent spots.
2. The two-dimensional airfoil wind tunnel test bench of claim 1, wherein said angle adjustment mechanism comprises an indexing disc and a three-jaw chuck;
the dividing disc is connected with the three-jaw chuck into a whole, and the rod balance is clamped through the three-jaw chuck.
3. The two-dimensional airfoil wind tunnel test bench of claim 2, wherein the bar balance is disposed in a horizontal direction.
4. A two-dimensional airfoil wind tunnel test bench according to claim 1 or 3, wherein said ramp is at an angle of 8-10 degrees to said floor.
5. The two-dimensional airfoil wind tunnel test bench according to claim 4, wherein two sides of the partition plate are symmetrically provided with diagonal bracing brackets.
6. The two-dimensional airfoil wind tunnel test bench according to claim 5, wherein the projected contour line of the curved surface in the horizontal direction sequentially comprises a first arc and a second arc which are tangent from the end of the partition plate to the inner side.
7. The two-dimensional airfoil wind tunnel test bench of claim 6 wherein said spacer has a thickness of 16mm; the curvature radius of the first arc is 10mm, and the corresponding central angle is 30-60 degrees; and two ends of the second circular arc are tangent to the first circular arc and the inner side surface of the partition plate respectively.
8. The two-dimensional airfoil wind tunnel test stand of claim 1, wherein when tested using a maximum angle of attack, the airfoil has a distance from the wind-facing end to the baffle wind-inlet end edge of:
X＝0.0001L 3 -0.075L 2 +16.952L-541.65；
where L is the height of the projection of the airfoil in the vertical direction at the maximum angle of attack.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201811416765.8A CN109540453B (en) | 2018-11-26 | 2018-11-26 | Wind tunnel test bench of two-dimensional wing section |
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| CN201811416765.8A CN109540453B (en) | 2018-11-26 | 2018-11-26 | Wind tunnel test bench of two-dimensional wing section |
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| CN109540453B true CN109540453B (en) | 2024-02-20 |
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| CN110530595A (en) * | 2019-07-19 | 2019-12-03 | 南京航空航天大学 | A kind of plane cascade test platform test section inlet system of the adjustable angle of attack |
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| CN102288381A (en) * | 2011-05-05 | 2011-12-21 | 西北工业大学 | Wing tip support device for wind tunnel test |
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