Wind tunnel airfoil experimental device

Abstract

The wind tunnel airfoil experiment device comprises a driving assembly, a follow-up assembly and an alignment piece. The driving assembly comprises a driving part and a clamp, the driving part provides driving force for dynamic motion of the wing-shaped part, the clamp is in transmission connection with the output end of the driving part so as to be driven by the driving part to rotate, a first positioning hole with a rhombic section is formed in the clamp, and the first positioning hole is provided with a first angular point and a second angular point which are opposite to each other; the first angular point and the second angular point are collinear with the center line of the wind tunnel, and the first positioning hole is used for embedding a rhombic positioning column at the first end of the airfoil profile and enabling the first angular point and the second angular point to be collinear with the wing chord of the airfoil profile. The follow-up assembly comprises a bearing piece, and an inner hole of the bearing piece serves as a second positioning hole allowing a positioning cylinder at the second end of the airfoil profile to be embedded. The alignment piece is arranged on the clamp and used for aligning the rotation axis of the first positioning hole with the rotation axis of the second positioning hole. According to the invention, accurate positioning of the zero attack angle position of the airfoil wind tunnel experiment can be carried out.

Description

Technical Field

[0001] The invention relates to the technical field of airfoil wind tunnel experimental testing, and more specifically to a wind tunnel airfoil experimental device. Background Art

[0002] Wind tunnel testing is an indispensable technical means in the aerodynamic design process of wind turbine airfoils. Usually, the wind turbine airfoil is fixed in the wind tunnel, and the aerodynamic data of the airfoil and the surrounding flow field information are obtained through testing technology, so as to analyze the aerodynamic performance of the airfoil and the flow state of the surrounding flow field. The performance of the wind turbine airfoil is greatly affected by the actual inflow angle of attack. The performance will change significantly with every degree change in the angle of attack. Therefore, only by accurately obtaining the actual inflow angle of attack of the airfoil in the wind tunnel experiment can accurate wind turbine airfoil performance data be obtained.

[0003] The main factors that affect the accuracy of the airfoil inflow angle of attack are as follows: (1) During the installation and fixing stage of the airfoil, it is usually necessary to make the airfoil chord (the line connecting the leading edge point and the trailing edge point) consistent with the wind tunnel inflow direction. However, in actual operation, it is difficult to accurately determine the position of the leading edge point and the trailing edge point with the naked eye, which will cause the initial position of the airfoil to be unable to accurately align with the wind tunnel inflow direction. (2) During the experiment, the airfoil needs to always keep the span direction (rotation axis) completely perpendicular to the inflow direction. It is difficult to ensure that the span direction is always perpendicular to the inflow direction when the airfoil is fixed at one end. In addition, during the frequent changes in the airfoil angle of attack, the rotation axis may be offset, which has a great impact on the accuracy of the aerodynamic force and flow field data. (3) At present, the adjustment of the airfoil angle of attack mostly adopts mechanical drive to achieve dynamic adjustment. These adjustment methods are difficult to meet the frequent and fast requirements, and thus it is difficult to ensure the accuracy of the angle of attack. In addition, mechanical transmission devices and human factors may also cause deviations between the actual angle of attack and the set value. Although using a servo motor to control the airfoil angle of attack can effectively improve the accuracy of rotational positioning, the zero drift problem of the servo motor can also cause the angle of attack to shift.

[0004] The above factors will lead to a significant decrease in the accuracy of the airfoil aerodynamic and flow field test data, resulting in significant errors in the test results. Therefore, how to accurately obtain the actual inflow angle of attack of the airfoil during the wind tunnel test to improve the accuracy of the test has become a technical problem that needs to be solved urgently by those skilled in the art.

[0005] SUMMARY OF THE INVENTION

[0006] In view of this, an object of the present invention is to provide a wind tunnel airfoil test device to accurately obtain the actual inflow angle of attack of the airfoil during a wind tunnel test, thereby improving the accuracy of the test.

[0007] To achieve the above object, the present invention provides the following technical solutions:

[0008] A wind tunnel airfoil test device is used for conducting an airfoil test in a wind tunnel, wherein the wind tunnel has a wind tunnel centerline and a first side wall and a second side wall opposite to each other, wherein the wind tunnel centerline is parallel to an inflow wind speed direction in the wind tunnel, and comprises:

[0009] A driving assembly, comprising a driving member and a fixture, wherein the driving member is used to be arranged on the first side wall, the fixture is drivingly connected to the output end of the driving member, the fixture is provided with a first positioning hole with a diamond-shaped cross section, the rotation axis of the first positioning hole coincides with the center line and is perpendicular to the center line of the wind tunnel, the first positioning hole has a first corner point and a second corner point opposite to each other, the first corner point and the second corner point are both used to be collinear with the center line of the wind tunnel, the first positioning hole is used for the diamond-shaped positioning column at the first end of the airfoil to be embedded, and the first corner point and the second corner point are both collinear with the chord of the airfoil;

[0010] A follower assembly, comprising a positioning bracket and a bearing member, wherein the positioning bracket is used to be arranged on the second side wall, the bearing member is arranged on the positioning bracket in an adjustable manner, and the inner hole of the bearing member is used as a second positioning hole for the positioning cylinder at the second end of the airfoil to be embedded, and the rotation axis of the second positioning hole coincides with the center line;

[0011] An alignment member is provided on the fixture and is used to align the rotation axis of the first positioning hole with the rotation axis of the second positioning hole.

[0012] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the alignment component is a laser alignment device, and the laser emission direction of the laser alignment device is colinear with the rotation axis of the first positioning hole.

[0013] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the first positioning hole is a step hole, the large diameter end of the first positioning hole is closer to the follower assembly than the small diameter end, the positioning piece is arranged in the small diameter end of the step hole, and the diamond positioning column is used to be embedded in the large diameter end of the step hole and positioned and matched with the step surface of the step hole.

[0014] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the positioning bracket includes:

[0015] An adjustment track, configured to be arranged on the second side wall;

[0016] A movable bracket is slidably arranged on the adjustment track along a first direction;

[0017] A bearing chuck is slidably arranged on the movable bracket along a second direction, and the bearing member is arranged on the bearing chuck, one of the first direction and the second direction is parallel to the center line of the wind tunnel, and the other is perpendicular to the center line of the wind tunnel.

[0018] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the positioning bracket further includes:

[0019] A first locking member, used to lock the position of the movable bracket on the adjustment track;

[0020] The second locking member is used to lock the position of the bearing chuck on the movable bracket.

[0021] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the first locking member includes a locking pin and / or a connecting bolt;

[0022] The second locking member includes a locking pin and / or a connecting bolt.

[0023] Optionally, in the above-mentioned wind tunnel airfoil experimental device, scales are provided on both the adjustment track and the movable bracket.

[0024] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the movable bracket is detachably arranged on the adjustment track, or the bearing chuck is detachably arranged on the movable bracket.

[0025] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the bearing component is arranged on the bearing chuck through a lifting assembly, and the lifting assembly is used to drive the bearing component to move in a direction close to or away from the fixture.

[0026] Optionally, in the above-mentioned wind tunnel airfoil experimental device, the driving component is a servo motor, and the servo motor is controlled by a speed pulse control signal sent by a motor controller.

[0027] The wind tunnel airfoil experimental device provided by the present invention includes a driving component, a follower component and a positioning component. The driving component includes a driving component and a fixture. The driving component is used to be arranged on the first side wall and provide driving force for the dynamic movement of the airfoil. The fixture is connected to the output end of the driving component by transmission so as to be driven to rotate by the driven component. A first positioning hole with a rhombus cross-section is arranged on the fixture. The first positioning hole has a first corner point and a second corner point relative to each other. The first corner point and the second corner point are both used to be collinear with the center line of the wind tunnel, and the first positioning hole is used for embedding the rhombus positioning column at the first end of the airfoil, and the first corner point and the second corner point are both collinear with the chord of the airfoil. The follower component includes a positioning bracket and a bearing component. The positioning bracket is used to be arranged on the second side wall of the wind tunnel. The position of the bearing component can be adjusted on the positioning bracket, and the inner hole of the bearing component is used as a second positioning hole for embedding the positioning cylinder at the second end of the airfoil. The center lines and the rotation axis of the first positioning hole and the second positioning hole are both collinear and perpendicular to the center line of the wind tunnel. The alignment member is arranged on the fixture, and is used to align the rotation axis of the first positioning hole with the rotation axis of the second positioning hole, so that the airfoil rotation axis of the airfoil is kept aligned with the center line of the wind tunnel.

[0028] Compared with the prior art, the wind tunnel airfoil experimental device provided by the present invention can realize the accurate fixed installation of the airfoil in the wind tunnel experiment, and complete the precise positioning of the zero angle of attack position of the airfoil in the wind tunnel experiment, so that the actual inflow angle of attack of the airfoil can be accurately obtained during the wind tunnel experiment, thereby improving the accuracy of the test; the present invention adopts a double-end fixing method to ensure that the span direction of the airfoil is always perpendicular to the wind tunnel inflow direction during the experiment, thereby improving the experimental accuracy and providing an effective means for accurately analyzing the aerodynamic characteristics and flow field characteristics of the airfoil. BRIEF DESCRIPTION OF THE DRAWINGS

[0029] In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings required for use in the embodiments or the description of the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0030] Figure 1 It is a schematic diagram of the assembly of a wind tunnel airfoil experimental device and an airfoil disclosed in an embodiment of the present invention;

[0031] Figure 2 A schematic diagram of the installation structure of the wind tunnel airfoil experimental device disclosed in an embodiment of the present invention in a wind tunnel;

[0032] Figure 3 It is a structural schematic diagram of a fixture disclosed in an embodiment of the present invention;

[0033] Figure 4 It is a schematic structural diagram of the first end of the airfoil disclosed in an embodiment of the present invention;

[0034] Figure 5 It is a schematic structural diagram of the second end of the airfoil disclosed in an embodiment of the present invention;

[0035] Figure 6 A control schematic diagram of a servo motor disclosed in an embodiment of the present invention;

[0036] Figure 7 It is a display diagram of the speed pulse control signal disclosed in an embodiment of the present invention;

[0037] Figure 8 This is a display diagram of the speed pulse control signal when the airfoil disclosed in an embodiment of the present invention moves to the maximum speed.

[0038] Among them, 10 is an airfoil, 11 is a diamond-shaped positioning column, 12 is a positioning cylinder, 20 is a driving member, 30 is a positioning bracket, 31 is a movable bracket, 32 is an adjustment track, 40 is a wind tunnel, 41 is a wind tunnel entrance, 42 is a second side wall, 43 is a first side wall, 50 is a bearing chuck, 51 is a bearing member, 60 is a fixture, 70 is a wind tunnel centerline, 71 is a center parallel line, and 80 is an airfoil rotating shaft. DETAILED DESCRIPTION

[0039] The core of the invention is to disclose a wind tunnel airfoil test device to accurately obtain the actual inflow angle of attack of the airfoil during the wind tunnel test, thereby improving the accuracy of the test.

[0040] The following embodiments are described with reference to the accompanying drawings. In addition, the embodiments shown below do not limit the contents of the present invention as described in the claims. In addition, the entire contents of the structures represented by the following embodiments are not limited to those necessary for the solutions of the present invention as described in the claims. It should be noted that, for ease of description, only the parts related to the present invention are shown in the accompanying drawings. In the absence of conflict, the embodiments of the present invention and the features in the embodiments can be combined with each other.

[0041] Combination Figure 1-Figure 6 The wind tunnel airfoil experimental device disclosed in the present invention is used to conduct experiments on an airfoil 10 in a wind tunnel 40. The wind tunnel 40 has a wind tunnel entrance 41, a wind tunnel centerline 70, and opposite first and second sidewalls 43 and 42. The wind tunnel entrance 41 is used for air intake. The wind tunnel centerline 70 can be set according to actual conditions. It only needs to ensure that the wind tunnel centerline 70 is parallel to the direction of the inflow wind speed in the wind tunnel 40. A diamond-shaped positioning column 11 with a diamond cross-section is provided at the first end of the airfoil 10, and a positioning cylinder 12 with a circular center cross-section is provided at the second end. The wind tunnel airfoil experimental device includes a driving component, a follower component, and a positioning member.

[0042] The driving assembly includes a driving member 20 and a clamp 60. The driving member 20 is used to be set on the first side wall 43 and provide driving force for the dynamic movement of the airfoil 10. The clamp 60 is transmission-connected to the output end of the driving member 20 so as to be driven to rotate by the driven member 20. A first positioning hole with a diamond-shaped cross-section is provided on the clamp 60. The first positioning hole has a first corner point and a second corner point relative to each other. The first corner point and the second corner point are both used to be collinear with the center line 70 of the wind tunnel, and the first positioning hole is used for the diamond-shaped positioning column 11 at the first end of the airfoil 10 to be embedded, and the first corner point and the second corner point are both collinear with the chord of the airfoil 10.

[0043] The follower assembly includes a positioning bracket 30 and a bearing member 51. The positioning bracket 30 is used to be set on the second side wall 42 of the wind tunnel 40. The bearing member 51 is adjusted on the positioning bracket 30, and the inner hole of the bearing member 51 is used as a second positioning hole for the positioning cylinder 12 at the second end of the airfoil 10 to be embedded. The center lines and rotation axes of the first positioning hole and the second positioning hole are both collinear and perpendicular to the wind tunnel center line 70. The alignment member is set on the fixture 60, and is used to align the rotation axis of the first positioning hole with the rotation axis of the second positioning hole, so that the airfoil rotation axis 80 of the airfoil 10 is kept aligned with the wind tunnel center line 70.

[0044] The fixture 60 is used to determine the zero angle of attack position of the airfoil 10. The fixture 60 and the bearing 51 together fix and adjust the position of the airfoil shaft 80 of the airfoil 10 and ensure that the airfoil shaft 80 of the airfoil 10 does not deviate during the experiment. Figure 3 The diamond shaped positioning column 11 has a third corner point A and a fourth corner point B relative to each other, and the third corner point A and the fourth corner point B are both collinear with the chord A'B' of the airfoil 10 (A' is the leading edge point, and B' is the trailing edge point). After the airfoil 10 is assembled with the fixture 60, the first corner point C and the second corner point D coincide with the third corner point A and the fourth corner point B respectively. When the first corner point C and the second corner point D are collinear with the wind tunnel centerline 70, the chord A'B' is also collinear with the wind tunnel centerline 70, thus confirming the zero angle of attack position of the airfoil 10. Figure 5 The center parallel line 71 is parallel to the wind tunnel center line 70 , and its intersection with the airfoil rotating shaft 80 coincides with a point of the positioning cylinder 12 .

[0045] Compared with the prior art, the wind tunnel airfoil experimental device disclosed in the present invention can realize the accurate fixed installation of the airfoil 10 in the wind tunnel experiment, and complete the precise positioning of the zero angle of attack position of the airfoil 10 in the wind tunnel experiment, so that the actual inflow angle of attack of the airfoil 10 can be accurately obtained during the wind tunnel experiment, thereby improving the accuracy of the test; the present invention adopts a double-end fixing method to ensure that the span direction of the airfoil 10 is always perpendicular to the inflow direction of the wind tunnel 40 during the experiment, thereby improving the experimental accuracy and providing an effective means for accurately analyzing the aerodynamic characteristics and flow field characteristics of the airfoil 10.

[0046] Specifically, the alignment member can be a laser alignment device, which is used to emit laser, and the laser emission direction of the laser alignment device is colinear with the rotation axis of the first positioning hole, so as to adjust the position of the bearing member 51 on the positioning bracket 30. The alignment member can also be a structure that can perform precise alignment, such as a visual recognition system. The alignment member can ensure that the fixture 60 and the bearing member 51 have the same rotation center line, so that the airfoil 10 will not generate internal stress during the rotation process.

[0047] In one embodiment, the first positioning hole is a stepped hole, and the large diameter end of the first positioning hole is closer to the follower assembly than the small diameter end. There is one laser alignment device, which is arranged in the small diameter end of the stepped hole, and the diamond positioning column 11 is used to be embedded in the large diameter end of the stepped hole and positioned with the step surface of the stepped hole to avoid interference with the diamond positioning column 11 while realizing the installation of the laser alignment device.

[0048] In order to adjust the position of the bearing member 51, in one embodiment, the positioning bracket 30 includes an adjustment track 32, a movable bracket 31 and a bearing chuck 50, the adjustment track 32 is used to be arranged on the second side wall 42, the movable bracket 31 is slidably arranged on the adjustment track 32 along a first direction; the bearing chuck 50 is slidably arranged on the movable bracket 31 along a second direction, and the bearing member 51 is arranged on the bearing chuck 50, one of the first direction and the second direction is parallel to the center line 70 of the wind tunnel, and the other is perpendicular to the center line 70 of the wind tunnel. By adjusting the position of the bearing chuck 50 on the movable bracket 31 and adjusting the position of the movable bracket 31 on the adjustment track 32, the position of the bearing member 51 can be adjusted.

[0049] Combination Figure 1 and Figure 2 For the convenience of description, the direction of the inflow wind speed is the X direction, the extending direction of the rotation axis of the first positioning hole and the second positioning hole is the Y direction, and the direction perpendicular to the X direction and the Y direction is the Z direction. The first direction and the second direction are parallel to one of the X direction and the Z direction respectively, that is, the bearing chuck 50 can drive the bearing member 51 to translate in a plane for position adjustment, and the plane is parallel to the ZX plane.

[0050] In addition, the positioning bracket 30 also includes a first locking member and a second locking member, wherein the first locking member is used to lock the position of the movable bracket 31 on the adjustment track 32; and the second locking member is used to lock the position of the bearing chuck 50 on the movable bracket 31, so as to prevent the airfoil rotating shaft 80 of the airfoil 10 from being deflected relative to the Y direction during the test. The first locking member and the second locking member can be bolts and / or locking pins, and corresponding connection holes and / or locking holes are opened on the adjustment track 32 and the movable bracket 31.

[0051] In order to avoid interference between the airfoil 10 and the positioning bracket 30 and the fixture 60 during the assembly process, the movable bracket can be detachably arranged on the adjustment track 32, or the bearing chuck 50 can be detachably arranged on the movable bracket 31, so that in the process of assembling the airfoil 10, the bearing component 51 and the bearing chuck 50 can be removed from the movable bracket 31 first, or the movable bracket 31, the bearing component 51 and the bearing chuck 50 can be removed from the adjustment track 32 together, and after the airfoil 10 and the fixture 60 are assembled, the bearing component 51 and the airfoil 10 can be assembled.

[0052] A further optimized solution is provided with scales on the adjustment track 32 and the movable bracket 31. During assembly, the position of the bearing component 51 is first adjusted by the alignment component so that the rotation axes of the first positioning hole and the second positioning hole are aligned. Then, the scale of the bearing chuck 50 on the movable bracket 31 and the scale of the movable bracket 31 on the adjustment track 32 are recorded. Then, the movable bracket 31, the bearing component 51 and the bearing chuck 50 are removed together to avoid affecting the assembly of the airfoil 10 and the fixture 60. After the assembly of the airfoil 10 and the fixture 60 is completed, the bearing component 51 and the airfoil 10 are assembled. Finally, the bearing chuck 50 and the movable bracket 31 are adjusted to the above-recorded positions respectively.

[0053] Alternatively, the bearing component 51 is arranged on the bearing chuck 50 through a lifting assembly (not shown in the figure), and the lifting assembly is used to drive the bearing component 51 to move in a direction close to or away from the fixture 60. After the position of the bearing component 51 is adjusted by the alignment member, the position of the bearing component 51 in the X direction and the Z direction is kept unchanged, and the lifting assembly raises the bearing component 51 along the Y direction to avoid the installation of the airfoil 10 on the fixture 60, and then drives the bearing component 51 to descend along the Y direction through the lifting assembly, so that the second positioning hole and the positioning cylinder 12 are embedded to complete the assembly.

[0054] The driving member 20 preferably adopts an AC servo motor and is equipped with a corresponding servo motor driver. The servo motor provides a driving force for the dynamic movement of the airfoil 10 to complete the adjustment of the angle of attack of the airfoil 10. In a specific embodiment disclosed in the present invention, a reducer is provided at the output end of the servo motor. After deceleration by the reducer, the adjustment accuracy of the output rotation angle of the servo motor can reach 0.01°. The reduction ratio of the reducer is 1:5. The maximum speed of the servo motor is 2000r / min, that is, the output speed of the servo motor after deceleration by the reducer can meet the requirement of 400r / min, and the servo motor is controlled by a speed pulse control signal, which can effectively avoid the zero drift problem of the servo motor. Figure 6 The servo motor of the wind tunnel airfoil experimental device of the present invention adopts a position control mode and is controlled by a dSpace control system. The speed pulse control signal in the control program is generated by the Simulink component system in MATLAB. The speed pulse control signal includes the displacement direction and displacement size. The Simulink system generates the underlying control program by calling the speed pulse program. On this basis, the dSpace control system calls the speed pulse control signal generated by the Simulink system and sends the speed pulse control signal to the servo motor controller, and then adjusts the rotation position and rotation speed of the servo motor through the controller to ensure that the airfoil 10 completes the dynamic movement according to the setting. Among them, the dSpace control system is mainly composed of two parts, namely the Control desk software control system and the ds1103 acquisition board hardware device.

[0055] Take the sinusoidal motion law of airfoil 10 as an example: the speed pulse generation program written by MATLAB is used, and the Simulink system calls the program to generate the speed pulse control signal. Figure 7 This is a display diagram of the speed pulse control signal. The black sine curve in the figure represents the displacement vector value of the motor output, and the green sine curve represents the vector value of the output speed. The airfoil 10 is at the minimum displacement at the initial position of the movement, and the output speed is zero. When the angle of attack of the airfoil 10 gradually increases, the speed value gradually increases. When the speed reaches the maximum value, the airfoil 10 runs to the center position of the sinusoidal pitch motion. Subsequently, the speed of the airfoil 10 gradually decreases. When the airfoil 10 moves to the maximum displacement position, the speed vector value returns to zero again, and the airfoil 10 starts to move in the opposite direction, repeating the same motion law. Figure 8 This is the display of the speed pulse control signal when the airfoil 10 moves to the maximum speed. By adjusting the sending time interval of the speed pulse control signal, the rotation speed of the driving member 20 can also be controlled.

[0056] It should be noted that the servo motor can also be controlled by other control systems. It only needs to ensure that the servo motor operates under the action of the speed pulse control signal to avoid the zero drift problem.

[0057] A specific test process of the present invention first determines the position of the wind tunnel centerline 70 according to the actual situation of the wind tunnel 40, that is, determines the direction of the inflow wind speed, in preparation for the subsequent determination of the zero-degree angle of attack position of the airfoil 10; adjusts the position of the fixture 60 so that it is located on the wind tunnel centerline 70, and then calibrates the second positioning hole through the alignment member, and adjusts the position of the bearing member 51 to ensure that the rotation axes of the first positioning hole and the second positioning hole are in line. Assemble the airfoil 10 to the wind tunnel airfoil experimental device, and ensure that the airfoil rotating shaft 80 of the airfoil 10 is parallel to the Y direction, so as to ensure that the span direction of the airfoil 10 is perpendicular to the inflow direction; finally, use the servo motor to adjust the position of the fixture 60 so that the first corner point and the second corner point are both in line with the wind tunnel centerline 70, and complete the determination of the zero-degree angle of attack position of the airfoil 10. During the wind tunnel experiment, the servo motor is driven by sending a speed pulse control signal to the motor controller, driving the airfoil 10 to complete dynamic rotation movements of different rules in the wind tunnel 40.

[0058] The above description of the disclosed embodiments enables professionals and technicians in the field to implement or use the present invention. Various modifications to these embodiments will be apparent to professionals and technicians in the field, and the general principles defined herein can be implemented in other embodiments without departing from the spirit or scope of the present invention. The specific technical means in some embodiments can be combined in part or in whole into another embodiment without being explicitly excluded by another embodiment. Therefore, the present invention will not be limited to the embodiments shown herein, but will conform to the widest range consistent with the principles and novel features disclosed herein.

Claims

1. A wind tunnel airfoil test device, used for conducting an airfoil (10) test in a wind tunnel (40), the wind tunnel (40) having a wind tunnel centerline (70) and a first side wall (43) and a second side wall (42) opposite to each other, the wind tunnel centerline (70) being parallel to an inflow wind speed direction in the wind tunnel (40), characterized in that: include: A drive assembly, comprising a drive member (20) and a fixture (60), wherein the drive member (20) is used to be arranged on the first side wall (43), the fixture (60) is drivingly connected to the output end of the drive member (20), and the fixture (60) is provided with a first positioning hole with a rhombus-shaped cross section, the rotation axis of the first positioning hole coincides with the center line and is perpendicular to the wind tunnel center line (70), the first positioning hole has a first corner point and a second corner point opposite to each other, the first corner point and the second corner point are both used to be collinear with the wind tunnel center line (70), the first positioning hole is used for the rhombus-shaped positioning column (11) at the first end of the airfoil (10) to be embedded, and the first corner point and the second corner point are both collinear with the chord of the airfoil (10); A follower assembly, comprising a positioning bracket (30) and a bearing member (51), wherein the positioning bracket (30) is used to be arranged on the second side wall (42), the bearing member (51) is arranged on the positioning bracket (30) in an adjustable manner, and an inner hole of the bearing member (51) is used as a second positioning hole for a positioning cylinder (12) at the second end of the airfoil (10) to be embedded, and the rotation axis of the second positioning hole coincides with the center line; An alignment member is provided on the fixture (60) and is used to align the rotation axis of the first positioning hole with the rotation axis of the second positioning hole.

2. The wind tunnel airfoil test device according to claim 1, characterized in that: The alignment member is a laser alignment device, and the laser emission direction of the laser alignment device is colinear with the rotation axis of the first positioning hole.

3. The wind tunnel airfoil test device according to claim 2, characterized in that: The first positioning hole is a stepped hole, the large diameter end of the first positioning hole is closer to the follower assembly than the small diameter end, the alignment member is arranged in the small diameter end of the stepped hole, and the diamond-shaped positioning column (11) is used to be embedded in the large diameter end of the stepped hole and positioned and matched with the stepped surface of the stepped hole.

4. The wind tunnel airfoil test device according to claim 1, characterized in that: The positioning bracket (30) comprises: An adjustment track (32) configured to be arranged on the second side wall (42); A movable bracket (31) is slidably arranged on the adjustment track (32) along a first direction; A bearing chuck (50) is slidably disposed on the movable bracket (31) along a second direction, and the bearing member (51) is disposed on the bearing chuck (50), wherein one of the first direction and the second direction is parallel to the wind tunnel centerline (70), and the other is perpendicular to the wind tunnel centerline (70).

5. The wind tunnel airfoil test device according to claim 4, characterized in that: The positioning bracket (30) further comprises: A first locking member, used for locking the position of the movable bracket (31) on the adjustment track (32); The second locking member is used to lock the position of the bearing chuck (50) on the movable bracket (31).

6. The wind tunnel airfoil test device according to claim 5, characterized in that: The first locking member includes a locking pin and / or a connecting bolt; The second locking member includes a locking pin and / or a connecting bolt.

7. The wind tunnel airfoil test device according to claim 4, characterized in that: The adjustment track (32) and the movable bracket (31) are both provided with scales.

8. The wind tunnel airfoil test device according to claim 4, characterized in that: The movable bracket is detachably arranged on the adjustment track (32), or the bearing chuck (50) is detachably arranged on the movable bracket (31).

9. The wind tunnel airfoil test device according to claim 4, characterized in that: The bearing component (51) is arranged on the bearing chuck (50) via a lifting assembly, and the lifting assembly is used to drive the bearing component (51) to move in a direction approaching or moving away from the fixture (60).

10. The wind tunnel airfoil test device according to claim 1, characterized in that: The driving component is a servo motor, and the servo motor is controlled by a speed pulse control signal sent by a motor controller.

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