A wind tunnel airfoil experiment device

Abstract

The wind tunnel airfoil experiment device disclosed by the application comprises a driving assembly, a following assembly and an alignment part. The driving assembly comprises a driving part and a clamp. The driving part provides driving force for dynamic movement of the airfoil. The clamp is drivingly connected to the output end of the driving part and is rotated by the driving part. A first positioning hole with a rhombic cross section is arranged on the clamp. The first positioning hole has opposite first and second corner points. The first and second corner points are used for being collinear with the center line of the wind tunnel. The first positioning hole is used for embedding a rhombic positioning column at the first end of the airfoil. The first and second corner points are collinear with the chord of the airfoil. The following assembly comprises a bearing part. The inner hole of the bearing part is used as a second positioning hole for embedding a positioning column at the second end of the airfoil. The alignment part is arranged on the clamp and is used for aligning the rotation axis of the first positioning hole with the rotation axis of the second positioning hole. The application can accurately position the zero angle of attack position of the airfoil wind tunnel experiment.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of airfoil wind tunnel test technology, and more particularly, to a wind tunnel airfoil test device. BACKGROUND

[0002] Wind tunnel test is an indispensable technical means in the process of wind turbine airfoil aerodynamic force design. Generally, the wind turbine airfoil is fixed in the wind tunnel, and the aerodynamic force data and surrounding flow field information of the airfoil are obtained through test 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, and the performance will change significantly with the change of one degree of the angle of attack. Therefore, only the actual inflow angle of attack of the airfoil can be accurately obtained in the wind tunnel test, the performance data of the wind turbine airfoil can be accurately obtained.

[0003] The main factors affecting the accuracy of the airfoil inflow angle of attack are as follows: (1) During the installation and fixation of the airfoil, the chord line (the line connecting the leading edge point and the trailing edge point) of the airfoil is usually required to be consistent with the direction of the wind tunnel inflow. However, in actual operation, it is difficult to accurately determine the positions of the leading edge point and the trailing edge point with the naked eye, which will result in that the initial position of the airfoil cannot be accurately aligned with the inflow direction of the wind tunnel. (2) During the test process, the airfoil needs to be kept vertical to the inflow direction at all times, and it is difficult to ensure that the spanwise (rotation axis) is always perpendicular to the inflow direction by using single-end fixation. In addition, during the process of frequent change of the airfoil angle of attack, the rotation axis may be offset, which has a great influence on the accuracy of the aerodynamic force and flow field data. (3) At present, the adjustment of the airfoil angle of attack is mostly realized by mechanical driving, which is difficult to meet the frequent and rapid requirements, so as to ensure the accuracy of the angle of attack. In addition, mechanical transmission devices and human factors may also cause deviation between the actual angle of attack and the set value. Although the servo motor is used to control the angle of attack of the airfoil, the zero drift problem of the servo motor may also cause the angle of attack to deviate.

[0004] The above factors will cause the accuracy of the airfoil aerodynamic force and flow field test data to decrease significantly, and the test results will have obvious errors. Therefore, how to accurately obtain the actual inflow angle of attack of the airfoil during the wind tunnel test process to improve the accuracy of the test has become a technical problem to be solved by the person skilled in the art.

[0005] SUMMARY

[0006] Therefore, the purpose of the present application is to provide a wind tunnel airfoil test device to accurately obtain the actual inflow angle of attack of the airfoil during the wind tunnel test process, and to improve the accuracy of the test.

[0007] To achieve the above-mentioned purpose, the present application provides the following technical scheme:

[0008] A wind tunnel airfoil experimental device for conducting an airfoil experiment in a wind tunnel, the wind tunnel having a wind tunnel centerline parallel to a direction of incoming flow velocity in the wind tunnel and opposite first and second sidewalls, comprising:

[0009] a driving assembly including a driving member and a fixture, the driving member configured to be disposed on the first sidewall, the fixture drivingly connected to an output end of the driving member, the fixture having a first positioning hole with a rhombus-shaped cross section, a rotation axis of the first positioning hole coinciding with the centerline and being perpendicular to the wind tunnel centerline, the first positioning hole having opposite first and second corner points, the first and second corner points each configured to be collinear with the wind tunnel centerline, the first positioning hole configured to receive a rhombus-shaped positioning column of a first end of an airfoil and to have the first and second corner points each collinear with a chord of the airfoil;

[0010] a following assembly including a positioning bracket and a bearing member, the positioning bracket configured to be disposed on the second sidewall, the bearing member adjustably disposed on the positioning bracket, and an inner hole of the bearing member configured to be a second positioning hole for receiving a positioning cylinder of a second end of the airfoil, a rotation axis of the second positioning hole coinciding with the centerline;

[0011] an alignment member disposed on the fixture and configured to align the rotation axis of the first positioning hole and the rotation axis of the second positioning hole.

[0012] Optionally, in the wind tunnel airfoil experimental device described above, the alignment member is a laser alignment device, a laser emission direction of the laser alignment device being collinear with the rotation axis of the first positioning hole.

[0013] Optionally, in the wind tunnel airfoil experimental device described above, the first positioning hole is a stepped hole, a large-diameter end of the first positioning hole being closer to the following assembly than a small-diameter end, the alignment member being disposed in the small-diameter end of the stepped hole, the rhombus-shaped positioning column being configured to be received in the large-diameter end of the stepped hole and to be positioned in cooperation with a stepped surface of the stepped hole.

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

[0015] an adjustment track configured to be disposed on the second sidewall;

[0016] a moving bracket slidably disposed on the adjustment track in a first direction;

[0017] a bearing chuck slidably disposed on the moving bracket in a second direction, and the bearing member being disposed on the bearing chuck, one of the first direction and the second direction being parallel to the wind tunnel centerline, and the other being perpendicular to the wind tunnel centerline.

[0018] Optionally, in the wind tunnel airfoil experimental device, the positioning support further comprises:

[0019] a first locking member for locking the position of the moving support on the adjusting track;

[0020] a second locking member for locking the position of the bearing chuck on the moving support.

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

[0022] the second locking member comprises a locking pin and / or a connecting bolt.

[0023] Optionally, in the wind tunnel airfoil experimental device, the adjusting track and the moving support are both provided with scales.

[0024] Optionally, in the wind tunnel airfoil experimental device, the moving support is detachably arranged on the adjusting track, or the bearing chuck is detachably arranged on the moving support.

[0025] Optionally, in the wind tunnel airfoil experimental device, the bearing member is arranged on the bearing chuck through a lifting assembly, and the lifting assembly is used to drive the bearing member to move towards or away from the fixture.

[0026] Optionally, in the wind tunnel airfoil experimental device, the driving assembly 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 comprises a driving assembly, a following assembly and an alignment member. The driving assembly comprises a driving member and a fixture. The driving member is arranged on a first side wall and provides driving force for dynamic movement of the airfoil. The fixture is drivingly connected to the output end of the driving member to be driven to rotate by the driving member. A first positioning hole with a rhombus cross section is arranged on the fixture. The first positioning hole has opposite first and second corner points. The first and second corner points are both used to be collinear with the center line of the wind tunnel. The first positioning hole is used to embed a rhombus positioning column at the first end of the airfoil, and the first and second corner points are both collinear with the chord of the airfoil. The following assembly comprises a positioning support and a bearing member. The positioning support is arranged on a second side wall of the wind tunnel. The bearing member is arranged on the positioning support in an adjustable manner. The inner hole of the bearing member is used as a second positioning hole for embedding a positioning column at the second end of the airfoil. The center lines of the first and second positioning holes and the rotation axis are all collinear with 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 shaft is kept perpendicular to the center line of the wind tunnel.

[0028] Compared with the prior art, the wind tunnel airfoil experiment device provided by the application can realize accurate fixing and installation of an airfoil in a wind tunnel experiment, complete accurate positioning of a zero angle of attack position of the airfoil wind tunnel experiment, and accurately obtain an actual inflow angle of the airfoil in the wind tunnel experiment, thereby improving the accuracy of the experiment; the double-end fixing mode adopted by the application can ensure that the airfoil span direction is always perpendicular to the wind tunnel inflow direction during the experiment, thereby improving the experimental precision and providing an effective means for accurately analyzing airfoil aerodynamic force characteristics and flow field characteristics. BRIEF DESCRIPTION OF DRAWINGS

[0029] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings needed to be used in the embodiments or the prior art description will be briefly introduced. Obviously, the drawings in the following description only constitute some embodiments of the present application, and other drawings can be obtained by those skilled in the art without creative effort on the basis of these drawings.

[0030] Figure 1 The wind tunnel airfoil experiment device disclosed by the embodiment of the present application and the assembly schematic diagram of the airfoil;

[0031] Figure 2 The installation structure schematic diagram of the wind tunnel airfoil experiment device disclosed by the embodiment of the present application in the wind tunnel;

[0032] Figure 3 The structure schematic diagram of the fixture disclosed by the embodiment of the present application;

[0033] Figure 4 The structure schematic diagram of the first end of the airfoil disclosed by the embodiment of the present application;

[0034] Figure 5 The structure schematic diagram of the second end of the airfoil disclosed by the embodiment of the present application;

[0035] Figure 6 The control schematic diagram of the servo motor disclosed by the embodiment of the present application;

[0036] Figure 7 The speed pulse control signal display diagram of the embodiment of the present application;

[0037] Figure 8 The speed pulse control signal display diagram of the airfoil moving to the maximum speed of the embodiment of the present application.

[0038] Wherein, 10 is a wing type, 11 is a rhombic positioning column, 12 is a positioning cylinder, 20 is a driving piece, 30 is a positioning support, 31 is a moving support, 32 is an adjusting track, 40 is a wind tunnel, 41 is a wind tunnel inlet, 42 is a second side wall, 43 is a first side wall, 50 is a bearing chuck, 51 is a bearing piece, 60 is a clamp, 70 is a wind tunnel center line, 71 is a center parallel line, and 80 is a wing type rotating shaft. DETAILED DESCRIPTION

[0039] The core of the present application is to disclose a wind tunnel wing type experiment device to accurately obtain the actual inflow attack angle of the wing type in the wind tunnel experiment process, thereby improving the accuracy of the experiment.

[0040] Hereinafter, the embodiments will be described with reference to the accompanying drawings. In addition, the embodiments shown below do not have any limiting effect on the content of the present application recited in the claims. In addition, the entire content of the configuration represented in the following embodiments is not limited to what is necessary as a solution to the present application recited in the claims. It should be noted that only the parts related to the present application are shown in the drawings for ease of description. In the case of no conflict, the embodiments in the present application and the features in the embodiments can be combined with each other.

[0041] In combination Figures 1-6 The wind tunnel wing type experiment device disclosed in the present application is used for the experiment of the wing type 10 in the wind tunnel 40, the wind tunnel 40 has a wind tunnel inlet 41, a wind tunnel center line 70 and opposite first and second side walls 43 and 42, the wind tunnel inlet 41 is used for air inlet, the wind tunnel center line 70 can be set according to the actual situation, only need to ensure that the wind tunnel center line 70 is parallel to the direction of the inflow wind speed in the wind tunnel 40, the first end of the wing type 10 is provided with a rhombic positioning column 11 with a rhombic cross section, and the second end is provided with a positioning cylinder 12 with a circular cross section, the wind tunnel wing type experiment device comprises a driving assembly, a following assembly and an alignment piece.

[0042] The driving assembly comprises a driving piece 20 and a clamp 60, the driving piece 20 is arranged on the first side wall 43 and provides driving force for the dynamic movement of the wing type 10, the clamp 60 is drivingly connected to the output end of the driving piece 20 to be driven to rotate by the driving piece 20, a first positioning hole with a rhombic cross section is arranged on the clamp 60, the first positioning hole has opposite first and second corner points, the first and second corner points are both used for being collinear with the wind tunnel center line 70, and the first positioning hole is used for embedding the rhombic positioning column 11 at the first end of the wing type 10, and the first and second corner points are both collinear with the chord of the wing type 10.

[0043] The follow-up assembly comprises a positioning support 30 arranged on the second side wall 42 of the wind tunnel 40 and a bearing member 51 arranged on the positioning support 30 in a position-adjustable manner, and an inner hole of the bearing member 51 is used as a second positioning hole for embedding the positioning cylinder 12 of the second end of the airfoil 10. The center lines of the first positioning hole and the second positioning hole are collinear with the rotation axis, and are perpendicular to the wind tunnel center line 70. The alignment member is arranged on the fixture 60 and is used for aligning 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 with the wind tunnel center line 70.

[0044] The fixture 60 plays a role in determining the zero angle of attack position of the airfoil 10, and the fixture 60 and the bearing member 51 jointly fix and adjust the position of the airfoil rotation axis 80 of the airfoil 10, and ensure that the airfoil rotation axis 80 of the airfoil 10 does not deviate during the experiment. Specifically, in combination with Figure 3 The rhombic positioning column 11 has opposite third and fourth corner points A and B, and the third and fourth corner points A and B are collinear with the chord A'B' of the airfoil 10 (A' is the leading edge point and B' is the trailing edge point), and after the airfoil 10 is assembled with the fixture 60, the first and second corner points C and D coincide with the third and fourth corner points A and B, respectively, and when the first and second corner points C and D are collinear with the wind tunnel center line 70, the chord A'B' is also collinear with the wind tunnel center line 70, thereby achieving the confirmation of the zero angle of attack position of the airfoil 10. In combination with Figure 5 The central parallel line 71 is parallel to the wind tunnel center line 70, and the intersection point of the central parallel line 71 and the airfoil rotation axis 80 coincides with a circular point of the positioning cylinder 12.

[0045] Compared with the prior art, the wind tunnel airfoil experiment device disclosed by the present application can accurately fix and install the airfoil 10 in the wind tunnel experiment, and accurately position the zero angle of attack position of the airfoil 10 in the wind tunnel experiment, so that the actual inflow angle of the airfoil 10 can be accurately obtained during the wind tunnel experiment, thereby improving the accuracy of the experiment; the double-end fixing method adopted by the present application can ensure that the spanwise direction of the airfoil 10 is always perpendicular to the inflow direction of the wind tunnel 40 during the experiment, thereby improving the experimental precision and providing an effective means for accurately analyzing the aerodynamic force characteristics and flow field characteristics of the airfoil 10.

[0046] Specifically, the alignment member can be a laser alignment device, the laser alignment device is used for emitting laser light, and the laser emission direction of the laser alignment device is collinear with the rotation axis of the first positioning hole, so as to adjust the position of the bearing member 51 on the positioning support 30. The alignment member can also be a visual recognition system or other structure that can accurately align. The alignment member can ensure that the fixture 60 and the bearing member 51 have the same rotation center line, thereby preventing internal stress of the airfoil 10 during rotation.

[0047] In an embodiment, 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 laser alignment device is one and is arranged in the small-diameter end of the stepped hole, and the rhombic positioning column 11 is used for embedding in the large-diameter end of the stepped hole and positioning and matching with the stepped surface of the stepped hole, so as to realize the installation of the laser alignment device and avoid the interference between the laser alignment device and the rhombic positioning column 11.

[0048] In order to realize the position adjustment of the bearing part 51, in an embodiment, the positioning support 30 comprises an adjustment track 32, a moving support 31 and a bearing chuck 50, the adjustment track 32 is arranged on the second side wall 42, the moving support 31 is slidably arranged on the adjustment track 32 in the first direction, the bearing chuck 50 is slidably arranged on the moving support 31 in the second direction, and the bearing part 51 is arranged on the bearing chuck 50, one of the first direction and the second direction is parallel to the wind tunnel center line 70, and the other is perpendicular to the wind tunnel center line 70. By adjusting the position of the bearing chuck 50 on the moving support 31 and adjusting the position of the moving support 31 on the adjustment track 32, the position adjustment of the bearing part 51 can be realized.

[0049] In combination with Figure 1 and Figure 2 , in order to facilitate the description, the incoming flow velocity direction is the X direction, the extension 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 respectively parallel to one of the X direction and the Z direction, that is, the bearing chuck 50 can drive the bearing part 51 to translate in a plane for position adjustment, and the plane is parallel to the ZX plane.

[0050] In addition, the positioning support 30 further comprises a first locking part and a second locking part, the first locking part is used for locking the position of the moving support 31 on the adjustment track 32, and the second locking part is used for locking the position of the bearing chuck 50 on the moving support 31, so as to avoid the relative Y direction deflection of the airfoil shaft 80 of the airfoil 10 in the test process. The first locking part and the second locking part can be bolts and / or locking pins, and corresponding connecting hole positions and / or locking hole positions are arranged on the adjustment track 32 and the moving support 31.

[0051] In order to avoid the interference between the airfoil 10 and the positioning support 30 and the clamp 60 in the assembly process, the moving support is detachably arranged on the adjustment track 32, or the bearing chuck 50 is detachably arranged on the moving support 31, so that in the process of assembling the airfoil 10, the bearing part 51 and the bearing chuck 50 can be taken off from the moving support 31, or the moving support 31, the bearing part 51 and the bearing chuck 50 can be taken off from the adjustment track 32 together, and after the airfoil 10 and the clamp 60 are assembled, the assembly of the bearing part 51 and the airfoil 10 is carried out.

[0052] Further optimization scheme, adjusting track 32 and mobile support 31 are provided with scales, in assembly, first, the position of bearing piece 51 is adjusted through alignment member, so that the rotation axes of first positioning hole and second positioning hole are aligned, then the scales of bearing chuck 50 on mobile support 31 and the scales of mobile support 31 on adjusting track 32 at this time are recorded, then mobile support 31, bearing piece 51 and bearing chuck 50 are taken down together to avoid affecting the assembly of airfoil 10 and fixture 60, after the assembly of airfoil 10 and fixture 60 is completed, the assembly of bearing piece 51 and airfoil 10 is carried out, finally, bearing chuck 50 and mobile support 31 are adjusted to the positions recorded above.

[0053] Or bearing piece 51 is arranged on bearing chuck 50 through lifting assembly (not shown in the figure), lifting assembly is used for driving bearing piece 51 to move towards the direction close to or away from fixture 60, after the position of bearing piece 51 is adjusted through alignment member, the position of bearing piece 51 in X direction and Z direction is kept unchanged, lifting assembly raises bearing piece 51 along Y direction to avoid the installation of airfoil 10 on fixture 60, then lifting assembly drives bearing piece 51 to descend along Y direction, so that second positioning hole is embedded with positioning cylinder 12, and the assembly is completed.

[0054] Driving member 20 preferably adopts alternating current servo motor, and corresponding servo motor driver is configured, driving force for dynamic motion of airfoil 10 is provided through servo motor to complete the angle of attack adjustment of airfoil 10.In a specific embodiment disclosed in the application, the output end of servo motor is provided with a speed reducer, after speed reduction through the speed reducer, the adjustment accuracy of the output rotation angle of servo motor can reach 0.01°, the speed reduction ratio of the speed reducer is 1:5, and the maximum rotation speed of the servo motor is 2000r / min, that is, the output rotation speed of the servo motor after speed reduction through the speed reducer can meet the requirement of 400r / min, and the servo motor is controlled by speed pulse control signal, so that the zero drift problem of the servo motor can be effectively avoided. Figure 6 In combination, the servo motor of the wind tunnel airfoil experiment device adopts position control mode, is controlled by dSpace control system, the speed pulse control signal in the control program is generated through Simulink component system in MATLAB, the speed pulse control signal includes displacement direction and displacement size, the speed pulse program is called through Simulink system, and then the bottom control program is generated, on this basis, the speed pulse control signal generated by Simulink system is called through dSpace control system, and the speed pulse control signal is sent to the servo motor controller, and then the rotation position and rotation speed of the servo motor are adjusted through the controller, so that the dynamic motion of airfoil 10 is completed according to the setting. The dSpace control system mainly consists of two parts, which are control desk software control system and ds1103 acquisition board card hardware device.

[0055] Taking the sinusoidal motion rule of the 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 The display diagram of the speed pulse control signal is shown in the figure, the black sinusoidal curve in the figure represents the displacement vector value of the motor output, and the green sinusoidal curve represents the vector value of the output speed, the airfoil 10 is at the minimum displacement at the initial position of the motion, and the output speed is zero, when the attack angle 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 pitching motion, then 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, and the same motion rule is repeated. Figure 8 The display diagram 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 control of the rotation speed of the driving member 20 can also be realized.

[0056] It should be noted that the servo motor can also be controlled by other control systems, as long as the servo motor is actuated under the action of the speed pulse control signal to avoid the zero drift problem.

[0057] In a specific test process of the present application, the position of the wind tunnel center line 70 is determined according to the actual situation of the wind tunnel 40, that is, the inflow wind speed direction is determined, which prepares for the subsequent determination of the zero attack angle position of the airfoil 10; the jig 60 is adjusted to be located on the wind tunnel center line 70, then the second positioning hole is calibrated by the positioning member, and the position of the bearing member 51 is adjusted to ensure that the rotation axes of the first positioning hole and the second positioning hole are collinear. The airfoil 10 is assembled to the wind tunnel airfoil experimental device, and the airfoil pivot 80 of the airfoil 10 is ensured to be parallel to the Y direction, so that the spanwise direction of the airfoil 10 is perpendicular to the inflow direction; finally, the servo motor is used to adjust the position of the jig 60 so that the first angle point and the second angle point are collinear with the wind tunnel center line 70, and the zero attack angle position of the airfoil 10 is determined. In the wind tunnel experiment process, the servo motor is driven by sending the speed pulse control signal to the motor controller, and the airfoil 10 completes different dynamic rotary motions in the wind tunnel 40.

[0058] The foregoing description of the disclosed embodiments enables a person skilled in the art to make or use the application. Modifications of these embodiments will occur to persons of skill in the art, and, while certain embodiments according to the principles set forth herein are shown and described, various modifications and substitutions can be made without departing from the spirit and scope of the application as set forth in the appended claims. Specific details in the described embodiments can be replaced with alternative details without departing from the spirit or scope of the application. Where a particular technical measure is described in a particular embodiment, that technical measure can be combined with other embodiments, in part or in whole, unless another embodiment specifically excludes such a combination. Thus, the application is not to be limited to the embodiments described herein but is to be accorded the widest scope consistent with the principles and novel features disclosed herein.

Claims

1. A wind tunnel airfoil experimental apparatus for conducting airfoil (10) experiments within a wind tunnel (40), the wind tunnel (40) having a wind tunnel centerline (70) and opposing first sidewalls (43) and second sidewalls (42), wherein the wind tunnel centerline (70) is parallel to the direction of the inflow wind velocity within the wind tunnel (40), characterized in that, The utility model relates to an air tunnel centering device, comprising: a driving assembly, comprising a driving part (20) arranged on the first side wall (43) and a fixture (60) drivingly connected to the output end of the driving part (20), the fixture (60) is provided with a first positioning hole with a rhombus cross section, the rotational axis of the first positioning hole coincides with the center line and is perpendicular to the air tunnel center line (70), the first positioning hole has opposite first and second corner points, both the first and second corner points are arranged to be collinear with the air tunnel center line (70), the first positioning hole is used for embedding a rhombus positioning column (11) at the first end of an airfoil (10) and making the first and second corner points collinear with the chord of the airfoil (10); a following assembly, comprising a positioning support (30) arranged on the second side wall (42) and a bearing part (51) arranged on the positioning support (30) in a position-adjustable manner, and the inner hole of the bearing part (51) is used as a second positioning hole for embedding a positioning cylinder (12) at the second end of the airfoil (10), and the rotational axis of the second positioning hole coincides with the center line; an alignment part arranged on the fixture (60) and used for aligning the rotational axes of the first and second positioning holes; the positioning support (30) comprises an adjusting track (32), a moving support (31) and a bearing chuck (50), the adjusting track (32) is arranged on the second side wall (42), the moving support (31) is slidably arranged on the adjusting track (32) in a first direction, and the bearing chuck (50) is slidably arranged on the moving support (31) in a second direction, and the bearing part (51) is arranged on the bearing chuck (50), one of the first and second directions is parallel to the air tunnel center line (70), and the other is perpendicular to the air tunnel center line (70).

2. The wind tunnel airfoil experiment apparatus of claim 1, wherein, The alignment part is a laser alignment device, and the laser emission direction of the laser alignment device is collinear with the rotational axis of the first positioning hole.

3. The wind tunnel airfoil experiment apparatus of claim 2, wherein, The first positioning hole is a stepped hole, the large-diameter end of the first positioning hole is closer to the following assembly than the small-diameter end, the alignment part is arranged in the small-diameter end of the stepped hole, the rhombus positioning column (11) is used for embedding the large-diameter end of the stepped hole and positioning and cooperating with the stepped surface of the stepped hole.

4. The wind tunnel airfoil experiment apparatus of claim 1, wherein, The positioning support (30) further comprises: a first locking part used for locking the position of the moving support (31) on the adjusting track (32); a second locking part used for locking the position of the bearing chuck (50) on the moving support (31).

5. The wind tunnel airfoil experiment apparatus of claim 4, wherein, The first locking part comprises a locking pin and / or a connecting bolt; The second locking part comprises a locking pin and / or a connecting bolt.

6. The wind tunnel airfoil experiment apparatus of claim 1, wherein, Both the adjusting track (32) and the moving support (31) are provided with scales.

7. The wind tunnel airfoil experiment apparatus of claim 1, wherein The moving support is detachably arranged on the adjusting track (32), or the bearing chuck (50) is detachably arranged on the moving support (31).

8. The wind tunnel airfoil experiment apparatus of claim 1, wherein, The bearing piece (51) is arranged on the bearing chuck (50) through a lifting assembly, which is used to drive the bearing piece (51) to move towards or away from the fixture (60).

9. The wind tunnel airfoil experiment apparatus of claim 1, wherein, The driving assembly 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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