Rotor wing type variable incoming flow dynamic stall test system

Abstract

The invention discloses a rotor wing type variable incoming flow dynamic stall test system, and relates to the technical field of airfoil aerodynamic performance, the rotor wing type variable incoming flow dynamic stall test system comprises an airflow module, an airfoil test sample section, a test platform and a base, the base is arranged below the test platform, at least one translation mechanism is arranged on the base, each translation mechanism is in transmission connection with the test platform, and the airfoil test sample section is arranged on the base. Each translation mechanism can drive the test platform to translate in the direction close to or away from the airflow module, the test platform is provided with an attack angle conversion mechanism, the attack angle conversion mechanism is in transmission connection with the wing-shaped test sample section and can drive the wing-shaped test sample section to do pitching motion, and the airflow module can provide constant-speed airflow for the wing-shaped test sample section; the rotor wing type variable incoming flow dynamic stall test can be smoothly carried out, and the rotor wing type variable incoming flow dynamic stall test device is simple in structure and convenient to use.

Description

Technical Field

[0001] The invention relates to the technical field of airfoil aerodynamic performance, in particular to a rotor airfoil variable flow dynamic stall test system. Background Art

[0002] The airfoil is the cross-sectional shape of an aircraft wing, tail wing, missile wing surface, helicopter rotor blade and propeller blade that is parallel to the aircraft symmetry plane or perpendicular to the leading edge (or the line connecting the 1 / 4 chord length points). It is also called the wing section or blade section.

[0003] In aerodynamics, an airfoil is usually understood as a two-dimensional wing, that is, an infinite span wing with a constant cross-sectional shape. When the airfoil moves relative to the air, the airfoil surface will be acted upon by the airflow. The component of the resultant force in the direction of the airfoil's movement or the incoming flow is the drag on the airfoil, and the component perpendicular to the above direction is the lift of the airfoil. The moment of these forces on the leading edge (or at a point 1 / 4 of the chord length from the leading edge) is called the pitch moment.

[0004] During the forward flight of a helicopter, the rotor airfoil faces an incoming flow with a constantly changing speed, so the aerodynamic performance is different from that of an airfoil with a constant incoming flow. If you want to conduct a dynamic stall test of a rotor airfoil with a variable incoming flow, you need to use a variable incoming flow wind tunnel to adjust the incoming flow speed during the test. However, variable incoming flow wind tunnels are relatively rare and have high technical requirements, making them inconvenient for studying the aerodynamic performance of airfoils with variable incoming flow. Summary of the invention

[0005] The object of the present invention is to provide a rotor airfoil variable flow dynamic stall test system to solve the problems existing in the above-mentioned prior art, to facilitate the smooth implementation of the rotor airfoil variable flow dynamic stall test, and to have a simple structure and be easy to use.

[0006] To achieve the above object, the present invention provides the following solutions:

[0007] The present invention provides a rotor airfoil variable flow dynamic stall test system, comprising an airflow module, an airfoil test sample section, a test platform and a base, wherein the base is placed below the test platform, and at least one translation mechanism is provided on the base, each of the translation mechanisms is transmission-connected with the test platform, and each of the translation mechanisms can drive the test platform to translate in a direction close to or away from the airflow module; an angle of attack conversion mechanism is provided on the test platform, and the angle of attack conversion mechanism is transmission-connected with the airfoil test sample section, and the angle of attack conversion mechanism can drive the airfoil test sample section to pitch, and the airflow module can provide a constant-speed airflow to the airfoil test sample section.

[0008] Preferably, the airflow module is a low-speed reflow wind tunnel.

[0009] Preferably, the angle of attack conversion mechanism includes an angle of attack conversion drive motor, a connecting rod and an angle of attack adjustment disk, the angle of attack conversion drive motor is arranged on the test platform, one end of the connecting rod is connected to the power output shaft of the angle of attack conversion drive motor, the other end of the connecting rod is connected to the angle of attack adjustment disk, and one end of the airfoil test sample segment is fixed on the angle of attack adjustment disk; the rotation of the power output shaft of the angle of attack conversion drive motor can drive the pitch movement of the airfoil test sample segment.

[0010] Preferably, the angle of attack conversion mechanism further includes a first support frame, the bottom end of the first support frame is fixedly connected to the test platform, and the top end of the first support frame is fixedly connected to the bottom end of the housing of the angle of attack conversion drive motor.

[0011] Preferably, the connecting rod includes a coupling and a driven shaft, one end of the coupling is fixedly connected to the power output shaft of the angle of attack conversion drive motor, the other end of the coupling is fixedly connected to one end of the driven shaft, and the other end of the driven shaft is fixedly connected to the angle of attack adjustment disk.

[0012] Preferably, the number of the translation mechanisms is two, and the two translation mechanisms act synchronously to make the test platform translate toward or away from the airflow module.

[0013] Preferably, the translation mechanism includes a translation drive device, a slider and a slide rail, the slide rail is fixed on the base, the top end of the slider is fixedly connected to the test platform, the bottom end of the slider extends into the slide rail, the slider can translate along the slide rail toward or away from the airflow module, the translation drive device is transmission-connected to the slider, and the translation drive device can provide power for the translation of the slider.

[0014] Preferably, the translational drive device includes a translational drive motor, an eccentric wheel, an eccentric shaft and a transmission rod, the translational drive motor is arranged on the base, the center of the eccentric wheel is fixedly connected to the power output shaft of the translational drive motor, one end of the eccentric shaft is fixedly connected to the edge of the eccentric wheel, the other end of the eccentric shaft is hinged to one end of the transmission rod, and the other end of the transmission rod is hinged to the slider; the rotation of the power output shaft of the translational drive motor can drive the slider to translate along the slide rail toward or away from the airflow module.

[0015] Preferably, the translation mechanism further includes a second support frame, the bottom end of the second support frame is fixedly connected to the base, and the top end of the second support frame is fixedly connected to the bottom end of the slide rail.

[0016] Preferably, the two translation mechanisms are symmetrically arranged.

[0017] Compared with the prior art, the present invention has achieved the following technical effects:

[0018] The rotor airfoil variable incoming flow dynamic stall test system provided by the present invention is provided with an airflow module to simulate an airflow environment so as to provide a constant-speed airflow to the airfoil test sample section, and the test platform is driven to translate in a direction close to or away from the airflow module by a translation mechanism located below the test platform, thereby changing the relative speed between the airfoil test sample section on the test platform and the airflow module. On the basis of the airflow module providing a constant-speed airflow to the airfoil test sample section, the airfoil test sample section translates with the test platform in a direction close to the airflow module, which is equivalent to speeding up the airflow and increasing the incoming flow speed, and the airfoil test sample section translates with the test platform in a direction away from the airflow module, which is equivalent to slowing down the airflow. Speed, reduce the incoming flow speed, realize real-time change of the actual incoming flow situation faced by the airfoil test sample section, realize the simulation of the variable incoming flow state of the rotor airfoil under the condition of a helicopter, so that the requirements for carrying out the dynamic stall test of the rotor airfoil with variable incoming flow are reduced, and it can be carried out under the condition of constant-speed airflow supplied by the airflow module. At the same time, the angle of attack conversion mechanism on the test platform can drive the pitch movement of the airfoil test sample section, so that the angle of attack of the airfoil test sample section changes regularly, ensuring the smooth implementation of the dynamic stall test of the rotor airfoil with variable incoming flow, including but not limited to carrying out fixed angle of attack variable incoming flow tests or variable angle of attack variable incoming flow tests, with simple structure, strong stability, low manufacturing difficulty and easy speed adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0019] 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 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.

[0020] Figure 1 A schematic diagram of a rotor airfoil variable flow dynamic stall test system provided by the present invention;

[0021] Figure 2 for Figure 1 Schematic diagram of the test platform and base;

[0022] In the figure: 1-airflow module, 2-airfoil test sample, 3-test platform, 4-base, 5-angle of attack change drive motor, 6-first support frame, 7-angle of attack adjustment disk, 8-coupling, 9-driven shaft, 10-slider, 11-slide rail, 12-translational drive motor, 13-eccentric wheel, 14-eccentric shaft, 15-transmission rod, 16-second support frame. DETAILED DESCRIPTION

[0023] The following will be combined with the drawings in the embodiments of the present invention to clearly and completely describe the technical solutions in the embodiments of the present invention. Obviously, the described embodiments are only part of the embodiments of the present invention, not all of the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0024] The object of the present invention is to provide a rotor airfoil variable flow dynamic stall test system to solve the problems existing in the above-mentioned prior art, to facilitate the smooth implementation of the rotor airfoil variable flow dynamic stall test, and to have a simple structure and be easy to use.

[0025] In order to make the above-mentioned objects, features and advantages of the present invention more obvious and easy to understand, the present invention is further described in detail below with reference to the accompanying drawings and specific embodiments.

[0026] like Figure 1 to Figure 2 As shown, the present invention provides a rotor airfoil variable flow dynamic stall test system, comprising an airflow module 1, an airfoil test sample section 2, a test platform 3 and a base 4, wherein the base 4 is placed below the test platform 3, and at least one translation mechanism is provided on the base 4, each translation mechanism is transmission-connected to the test platform 3, and each translation mechanism can drive the test platform 3 to translate toward or away from the airflow module 1, and an angle of attack conversion mechanism is provided on the test platform 3, and the angle of attack conversion mechanism is transmission-connected to the airfoil test sample section 2, and the angle of attack conversion mechanism can drive the airfoil test sample section 2 to pitch, and the airflow module 1 can provide a constant-speed airflow to the airfoil test sample section 2.

[0027] The rotor airfoil variable incoming flow dynamic stall test system provided by the present invention is provided with an airflow module 1 to simulate an airflow environment so as to provide a constant-speed airflow to the airfoil test sample section 2, and the test platform 3 is driven to translate in a direction close to or away from the airflow module 1 through a translation mechanism located below the test platform 3, thereby changing the relative speed between the airfoil test sample section 2 on the test platform 3 and the airflow module 1. On the basis that the airflow module 1 provides a constant-speed airflow to the airfoil test sample section 2, the airfoil test sample section 2 translates with the test platform 3 in a direction close to the airflow module 1, which is equivalent to speeding up the airflow and increasing the incoming flow speed. The airfoil test sample section 2 translates with the test platform 3 in a direction away from the airflow module 1, which is equivalent to speeding up the airflow and increasing the incoming flow speed. It is equivalent to slowing down the airflow, reducing the incoming flow speed, realizing real-time change of the actual incoming flow situation faced by the airfoil test sample section 2, realizing the simulation of the variable incoming flow state of the rotor airfoil under the condition of a helicopter, so that the requirements for carrying out the dynamic stall test of the rotor airfoil with variable incoming flow are reduced, and it can be carried out under the condition that the airflow module 1 supplies a constant-speed airflow. At the same time, the angle of attack conversion mechanism on the test platform 3 can drive the pitch movement of the airfoil test sample section 2, so that the angle of attack of the airfoil test sample section 2 changes regularly, ensuring the smooth implementation of the dynamic stall test of the rotor airfoil with variable incoming flow, including but not limited to carrying out a fixed angle of attack variable incoming flow test or a variable angle of attack variable incoming flow test, with a simple structure, strong stability, low manufacturing difficulty, and easy speed adjustment.

[0028] As a more preferred implementation of this embodiment, the airflow module 1 is a low-speed reflow wind tunnel, and the existing low-speed reflow wind tunnel can be used, which can effectively reduce the difficulty of conducting the test and improve the test efficiency.

[0029] As a more preferred implementation manner of this embodiment, the angle of attack change mechanism includes an angle of attack change drive motor 5, a connecting rod and an angle of attack adjustment disk 7. The angle of attack change drive motor 5 is arranged on the test platform 3, one end of the connecting rod is connected to the power output shaft of the angle of attack change drive motor 5, and the other end of the connecting rod is connected to the angle of attack adjustment disk 7. One end of the airfoil test sample 2 is fixed on the angle of attack adjustment disk 7; the rotation of the power output shaft of the angle of attack change drive motor 5 can drive the pitch movement of the airfoil test sample 2. The structure is simple, easy to manufacture, and easy to adjust the angle of attack change speed.

[0030] As a more preferred implementation manner of this embodiment, the angle of attack change mechanism also includes a first support frame 6, the bottom end of the first support frame 6 is fixedly connected to the test platform 3, and the top end of the first support frame 6 is fixedly connected to the bottom end of the shell of the angle of attack change drive motor 5, so as to increase the installation height of the angle of attack change drive motor 5 and reduce the difficulty of layout. As a more preferred implementation manner of this embodiment, the first support frame 6 adopts a rectangular steel frame with a simple structure, strong stability and easy manufacturing.

[0031] As a more preferred implementation scheme of this embodiment, the connecting rod includes a coupling 8 and a driven shaft 9. One end of the coupling 8 is fixedly connected to the power output shaft of the angle of attack conversion drive motor 5, the other end of the coupling 8 is fixedly connected to one end of the driven shaft 9, and the other end of the driven shaft 9 is fixedly connected to the angle of attack adjustment disk 7. The connection is stable and easy to use.

[0032] As a more preferred implementation of this embodiment, the translation mechanisms are evenly arranged to facilitate stable force transmission to the test platform 3.

[0033] As a more preferred implementation of this embodiment, there are two translation mechanisms, and the two translation mechanisms act synchronously to allow the test platform 3 to translate toward or away from the airflow module 1. The structure is simple and easy to manufacture and use.

[0034] As a more preferred implementation scheme of this embodiment, the translation mechanism includes a translation drive device, a slider 10 and a slide rail 11. The slide rail 11 is fixed on the base 4. The top of the slider 10 is fixedly connected to the test platform 3. The bottom end of the slider 10 extends into the slide rail 11. The slider 10 can translate along the slide rail 11 toward or away from the airflow module 1. The translation drive device is transmission-connected to the slider 10. The translation drive device can provide power for the translation of the slider 10, so as to facilitate guiding the slider 10 through the slide rail 11, thereby improving the movement stability of the test platform 3.

[0035] As a more preferred implementation scheme of this embodiment, the translational drive device includes a translational drive motor 12, an eccentric wheel 13, an eccentric shaft 14 and a transmission rod 15. The translational drive motor 12 is arranged on the base 4. The center of the eccentric wheel 13 is fixedly connected to the power output shaft of the translational drive motor 12, one end of the eccentric shaft 14 is fixedly connected to the edge of the eccentric wheel 13, the other end of the eccentric shaft 14 is hinged to one end of the transmission rod 15, and the other end of the transmission rod 15 is hinged to the slider 10; the rotation of the power output shaft of the translational drive motor 12 can drive the slider 10 to translate along the slide rail 11 in a direction close to or away from the airflow module 1. The structure is simple, easy to manufacture, and easy to adjust the translation speed of the test platform 3.

[0036] As a more preferred implementation of this embodiment, the translation mechanism also includes a second support frame 16, the bottom end of the second support frame 16 is fixedly connected to the base 4, and the top end of the second support frame 16 is fixedly connected to the bottom end of the slide rail 11, so as to increase the installation height of the slide rail 11 and reduce the difficulty of layout.

[0037] As a more preferred implementation of this embodiment, the two translation mechanisms are symmetrically arranged to facilitate stable force transmission to the test platform 3 and improve the movement stability of the test platform 3.

[0038] As a preferred implementation of this embodiment, the airfoil test sample 2 is fixedly mounted on the angle of attack adjustment disk 7 of the angle of attack change mechanism above the test platform 3, and the airflow module 1 is started, and the airflow module 1 provides a constant speed airflow to the airfoil test sample 2, so that the airflow speed is fixed at Ma 0 When the airfoil test sample 2 needs to translate along with the test platform 3 toward or away from the airflow module 1, the translation drive motor 12 in the translation mechanism below the test platform 3 is controlled to control the airfoil test sample 2 to translate toward or away from the airflow module 1, wherein the reciprocating motion of the slider 10 in the slide rail 11 is mainly achieved by controlling the frequency, phase and amplitude output of the translation drive motor 12 to drive the reciprocating motion of the test platform 3 above the slider 10, and the airfoil test sample 2 is fixed on the angle of attack adjustment disk 7 of the angle of attack conversion mechanism above the test platform 3, so the airfoil test sample 2 can realize reciprocating motion along with the reciprocating movement of the test platform 3. It should be noted that two translation mechanisms are provided below the test platform 3, and the frequency, phase and amplitude output of the translation drive motors 12 of the two translation mechanisms should be consistent.

[0039] Ma=Ma 0 +Ma m sin(ωt)

[0040] Among them, 0 is the speed of the constant-speed airflow provided by the airflow module 1 to the airfoil test sample section 2, Ma m is the velocity amplitude of the translation of the airfoil test sample 2, that is, the movement amplitude of the slider 10. The control purpose is achieved by adjusting the amplitude output of the translational drive motor 12. The airfoil test sample 2 translates with the test platform 3 in the direction close to the airflow module 1, which is equivalent to speeding up the airflow and increasing the incoming flow velocity. The airfoil test sample 2 translates with the test platform 3 in the direction away from the airflow module 1, which is equivalent to decelerating the airflow and reducing the incoming flow velocity. ω is the frequency of the translational movement speed change of the airfoil test sample 2, that is, the frequency of the movement speed change of the slider 10. The control purpose is achieved by adjusting the frequency of the translational drive motor 12. t is the test time.

[0041] In order to achieve the sine of the translational motion of the airfoil test specimen 2, the speed of the slider 10 should be:

[0042] v s (t) = Ma m sin(ωt)

[0043] The output relationship between the slider 10 and the translation drive motor 12 is as follows:

[0044] The length of the transmission rod 15 is L, the eccentricity (the distance from the center of the eccentric shaft 14 to the center of the eccentric wheel 13) is R, the translation drive motor 12 drives the eccentric wheel 13 to rotate, and the angular velocity of the eccentric wheel 13 is ω e(t) = ω e sin(ωt), angular velocity ω of the transmission rod 15 c as follows:

[0045]

[0046] The speed of the slider 10 is calculated from the angular velocity of the transmission rod 15:

[0047]

[0048] Right now

[0049]

[0050] It can be obtained from the above formula that the translation speed change of the airfoil test sample section 2 for different variable flow test requirements can be adjusted by adjusting the output frequency and angular velocity of the translation drive motor 12.

[0051] The length of the slide rail 11 can be obtained by integrating the velocity:

[0052]

[0053] The following is an example:

[0054] A certain fixed flow wind tunnel (i.e., airflow module 1) has a test section length of 5m and height of 2m, an incoming flow velocity of 40m / s, and a variable incoming flow test target of an average incoming flow of 40m / s with a velocity variation amplitude of 20m / s.

[0055] The angle of attack of the airfoil test sample section 2 changes to α=10°-10°sin(ωt), the chord length of the airfoil is 0.15m, the reduction frequency is k=0.124, the eccentricity R=0.5m, and the length of the transmission rod 15 is L=0.5m.

[0056] Then the output angular velocity amplitude of the translation drive motor 12 is as follows:

[0057] ω e =Ma m *R / L=20*0.5 / 0.5=20rad / s

[0058] Then the maximum unidirectional displacement of the airfoil test sample section 2 is obtained as:

[0059]

[0060] Then the forward and backward displacement of the slider 10, i.e. the length of the slide rail 11, is:

[0061] Δx=1.21m.

[0062] When the angle of attack of the airfoil test sample section 2 needs to be changed, the frequency, phase and amplitude output of the angle of attack change drive motor 5 in the angle of attack change mechanism can be adjusted to drive the airfoil test sample section 2 to have the following regular pitching motion:

[0063]

[0064] where α 0 is the initial installation angle of the airfoil test specimen 2 installed on the angle of attack adjustment plate 7, α m is the angle of attack amplitude in the pitching motion of the airfoil test sample segment 2, which can be controlled by adjusting the amplitude output of the angle of attack conversion drive motor 5; ω is the angular velocity of the angle of attack change in the pitching motion of the airfoil test sample segment 2, which can be controlled by adjusting the frequency of the angle of attack conversion drive motor 5; φ is the phase difference between the angle of attack change of the airfoil test sample segment 2 and the change of the incoming flow velocity of the airfoil test sample segment 2, which can be achieved by adjusting the phase difference between the angle of attack change drive motor 5 in the angle of attack conversion mechanism and the translation drive motor 12 in the translation mechanism; t is the test time.

[0065] Consistent with the above, the pitching motion of the airfoil test sample section 2 is the sinusoidal motion of the angle of attack adjustment disk 7. In order to make the rotation angle of the angle of attack adjustment disk 7 present a sinusoidal motion, the relationship between its rotation angle and the output angular velocity of the angle of attack conversion drive motor 5 is as follows:

[0066] α(t)=∫ω e (t)dt

[0067] That is, the angle of attack conversion drive motor 5 should output:

[0068] ω e (t) = ω e cos(ωt)

[0069] The angle change of the angle of attack adjustment plate 7 is as follows:

[0070]

[0071] in That is α m .

[0072] The present invention uses specific examples to illustrate the principles and implementation methods of the present invention. The above examples are only used to help understand the method and core ideas of the present invention. At the same time, for those skilled in the art, according to the ideas of the present invention, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A rotor airfoil variable flow dynamic stall test system, characterized in that: The invention comprises an airflow module, an airfoil test sample, a test platform and a base, wherein the base is placed below the test platform, and at least one translation mechanism is arranged on the base, each of which is transmission-connected with the test platform, and each of which can drive the test platform to translate toward or away from the airflow module. An angle of attack changing mechanism is arranged on the test platform, and the angle of attack changing mechanism is transmission-connected with the airfoil test sample, and the angle of attack changing mechanism can drive the airfoil test sample to pitch, and the airflow module can provide a constant-speed airflow to the airfoil test sample.

2. The rotor airfoil variable flow dynamic stall test system according to claim 1, characterized in that: The airflow module is a low-speed reflow wind tunnel.

3. The rotor airfoil variable flow dynamic stall test system according to claim 1, characterized in that: The angle of attack conversion mechanism includes an angle of attack conversion drive motor, a connecting rod and an angle of attack adjustment disk. The angle of attack conversion drive motor is arranged on the test platform, one end of the connecting rod is connected to the power output shaft of the angle of attack conversion drive motor, and the other end of the connecting rod is connected to the angle of attack adjustment disk. One end of the airfoil test sample is fixed on the angle of attack adjustment disk; the rotation of the power output shaft of the angle of attack conversion drive motor can drive the pitch movement of the airfoil test sample.

4. The rotor airfoil variable flow dynamic stall test system according to claim 3, characterized in that: The angle of attack conversion mechanism also includes a first support frame, the bottom end of the first support frame is fixedly connected to the test platform, and the top end of the first support frame is fixedly connected to the bottom end of the shell of the angle of attack conversion drive motor.

5. The rotor airfoil variable flow dynamic stall test system according to claim 3, characterized in that: The connecting rod includes a coupling and a driven shaft, one end of the coupling is fixedly connected to the power output shaft of the angle of attack conversion drive motor, the other end of the coupling is fixedly connected to one end of the driven shaft, and the other end of the driven shaft is fixedly connected to the angle of attack adjustment disk.

6. The rotor airfoil variable flow dynamic stall test system according to claim 1, characterized in that: The number of the translation mechanisms is two, and the two translation mechanisms act synchronously to make the test platform translate toward or away from the airflow module.

7. The rotor airfoil variable flow dynamic stall test system according to claim 6, characterized in that: The translation mechanism includes a translation drive device, a slider and a slide rail. The slide rail is fixed on the base. The top end of the slider is fixedly connected to the test platform. The bottom end of the slider extends into the slide rail. The slider can translate along the slide rail toward or away from the airflow module. The translation drive device is transmission-connected to the slider, and the translation drive device can provide power for the translation of the slider.

8. The rotor airfoil variable flow dynamic stall test system according to claim 7, characterized in that: The translational drive device includes a translational drive motor, an eccentric wheel, an eccentric shaft and a transmission rod. The translational drive motor is arranged on the base. The center of the eccentric wheel is fixedly connected to the power output shaft of the translational drive motor, one end of the eccentric shaft is fixedly connected to the edge of the eccentric wheel, the other end of the eccentric shaft is hinged to one end of the transmission rod, and the other end of the transmission rod is hinged to the slider; the rotation of the power output shaft of the translational drive motor can drive the slider to translate along the slide rail toward or away from the airflow module.

9. The rotor airfoil variable flow dynamic stall test system according to claim 8, characterized in that: The translation mechanism further includes a second support frame, the bottom end of the second support frame is fixedly connected to the base, and the top end of the second support frame is fixedly connected to the bottom end of the slide rail.

10. The rotor airfoil variable flow dynamic stall test system according to claim 9, characterized in that: The two translation mechanisms are symmetrically arranged.

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