Integrated wind tunnel test apparatus and method for coupling rotational and lateral jet streams

Abstract

The application provides a rotary and lateral jet coupling integrated wind tunnel test device and method, and belongs to the field of aerodynamics and flight control. The device comprises a test model, a balance support rod, a gas supply shaft, a gas supply head, a sliding sealing ring, a rolling servo motor, a shaft servo motor and a high-pressure gas supply channel. The test model is fixedly connected with the balance support rod and can rotate under the driving of the rolling servo motor, and the gas supply shaft penetrates through the model and delivers high-pressure gas to the gas supply head. The gas supply head and the model nozzle form a sliding fit, the relative position change realizes the periodic opening and closing of the jet, and the jet action range and time can be adjusted by the swing of the gas supply shaft. The device can simulate the rotation of the projectile body and the lateral jet action in the wind tunnel synchronously, has the advantages of fast response, high control precision and good similarity, and can be used for studying the aerodynamic and jet coupling mechanism of the rotary aircraft.

Description

Technical Field

[0001] This invention belongs to the field of aerodynamics and flight control, specifically relating to an integrated wind tunnel test device and method that couples rotation and lateral jet flow. Background Technology

[0002] Employing a combined lateral jet and direct airflow control system is the most direct and effective method to achieve agile maneuverability in aircraft. Combining lateral jets with a rotational mechanism can solve the problem of 360° jet force output, achieving full-domain energy optimization. This approach offers advantages such as low cost, high reliability, and strong all-domain compatibility, making it a crucial technical means to improve aircraft response speed and overload capacity. However, aircraft rotation causes significant aerodynamic coupling and unsteady flow phenomena. After coupling with lateral jet interference, complex vortex and wave flow field structures are formed around the nozzle and upstream and downstream, making the flow more complex. Therefore, wind tunnel testing is needed to obtain accurate jet effect data to better guide the design of its aerodynamic layout and control system.

[0003] However, simultaneously simulating projectile rotation and lateral jet effects in a wind tunnel is extremely difficult. One challenge lies in the high control dimensionality and the need for precise timing matching between the jet effect and the projectile's rolling motion, which are strongly coupled. Another challenge is that when the projectile's rotational speed is high, the jet effect duration must be short to ensure efficiency, placing extremely high demands on jet switch control. Currently, there are no reports, either domestically or internationally, on wind tunnel testing techniques that couple rotation and lateral jet effects.

[0004] Currently, in the relevant existing technologies: A Chinese patent application with publication number CN121877330A discloses a rotating jet interference wind tunnel test system and method. The system includes a rotation drive and support subsystem, a high-precision force measurement and control subsystem, and a rotating jet generation system. It achieves active and controllable rotation of the test model in the wind tunnel, real-time synchronous and accurate measurement of six-component aerodynamic forces / torques during rotation, and a stable supply of high-pressure jets via a hollow main shaft and a rotating sealed joint. The test method is based on simulation criteria of pressure ratio, momentum ratio, and Strouhal number similarity. By adjusting the model rotation speed, incoming Mach number, and jet pressure ratio, it systematically studies the unsteady aerodynamic interference law of rotation and jet coupling. However, this technology requires the jet to operate briefly in a given phase to generate force in a specific direction. If the jet continues to act, the equivalent resultant force of the jet is zero after one rotation of the projectile, making effective maneuverability impossible. Furthermore, this technology can only adjust the jet pressure ratio and cannot simulate the jet's operating time or the sequential opening of multiple nozzles.

[0005] To address the aforementioned problems, this invention proposes an integrated wind tunnel testing device and method that couples rotation and lateral jet flow. By using a motor-driven model rotation and a sliding air supply head, high-pressure gas is switched on and off. The high-pressure gas is then ejected through nozzles on the model, simulating the effect of lateral jet flow. This device and method ingeniously achieve the joint simulation of rotation and lateral jet flow, providing a solution for lateral jet flow wind tunnel testing of rotating aircraft and holding significant importance for the development and application of direct-air composite control technology for new equipment. Summary of the Invention

[0006] To address the shortcomings of existing technologies, the purpose of this invention is to provide an integrated wind tunnel testing device and method that couples rotation and lateral jet flow.

[0007] The integrated wind tunnel test device for rotation and lateral jet coupling provided by the present invention includes: a test model, a balance support rod, a gas supply mandrel, a rolling servo motor, a mandrel servo motor, a high-pressure gas supply channel, and a gas supply head; The test model is fixedly connected to the balance support rod; The rolling servo motor is connected to the balance support rod for transmission, and is used to drive the test model and the balance support rod to roll around the axis. Both the test model and the balance support rod are hollow structures, and the air supply mandrel passes through the hollow channel of the test model and the balance support rod along the axis of the hollow structure. One end of the air supply mandrel is fixedly connected to the air supply head, and the other end is connected to the mandrel servo motor. The mandrel servo motor is used to drive the air supply mandrel to lock or swing within a limited angle. The air supply head has an air supply head slot, and the test model is equipped with a model nozzle corresponding to the position of the air supply head slot. The high-pressure gas supply channel is connected to the gas supply mandrel to form a high-pressure gas delivery path; when the test model rolls, the relative position of the model nozzle and the slotted gas supply head changes periodically to realize the periodic on and off of the jet flow, and the swing of the gas supply mandrel adjusts the range and time of the jet flow. The high-pressure gas supply channel delivers high-pressure gas at a pressure of 1 MPa to 10 MPa.

[0008] Preferably, the integrated wind tunnel test device coupling rotation and lateral jet flow is characterized in that it further includes multiple sliding sealing rings; The sliding sealing ring is set between the air supply head and the model nozzle to achieve an airtight seal around the slot of the air supply head.

[0009] Preferably, the sliding sealing ring is annular, and there are two of them. They are respectively installed on both sides of the air supply head slot and the model nozzle wall, and slide and rub against the model nozzle to form a cylindrical sealing space.

[0010] Preferably, the dimensions within the throat diameter of the model nozzle match the slot of the air supply head.

[0011] Preferably, the gap between the air supply mandrel and the hollow inner wall of the test model and the balance support rod is not less than 1.5 mm.

[0012] The integrated wind tunnel testing method for rotational and lateral jet coupling provided by the present invention is implemented using the integrated wind tunnel testing apparatus for rotational and lateral jet coupling provided by the present invention, and includes: Step S1: Install the test model and test device, and adjust the test model to the initial zero position. At this time, the high-pressure gas is sealed and the jet is closed. Step S2: Start the data acquisition system and wind tunnel, and turn on the high-pressure gas supply after the flow field stabilizes; Step S3: Drive the test model to rotate by a rolling servo motor, and periodically align the model nozzle with the slotted air supply head to achieve periodic on and off of the jet flow; adjust the swing angle of the air supply mandrel by a mandrel servo motor to adjust the working fan area and working time of the jet flow. Step S4: After collecting data from multiple cycles of the experiment, stop the experiment.

[0013] Preferably, in step S1, the installation direction of the air supply head slot is directly opposite the plane of attack of the aircraft.

[0014] Preferably, in step S3: the control model rotates at the test speed under the drive of the rolling servo motor, and the nozzle of each model sprays once for each rotation. The working sector shape of the nozzle is determined by the slot width of the air supply head and the slot width of the mating surface of the model nozzle. Assuming the diameter of the mating surface is... The width of the gas supply head slot Groove width of the nozzle mating surface of the model The model rotation speed is When the air supply spindle is locked, the angle of the jet working sector is... for:

[0015] Jet working time for:

[0016] Adjust the size of the jet's working sector area to control the jet's effective range within the air supply spindle at a speed of [missing information]. Rotate, rotation angle is Then the angle of the jet working sector The adjustment is now as follows: .

[0017] Preferably, in step S4, the step of stopping the test operation includes: Step S41: Control the model rotation speed to zero; Step S42: Shut down the high-pressure gas; Step S43: Stop the wind tunnel; Step S44: Stop data acquisition.

[0018] Compared with the prior art, the present invention has the following beneficial effects: 1. This invention achieves the periodic on / off of high-pressure gas through the relative rotational motion of the model and the air supply mandrel, as well as the matching structure of the slotted air supply head and the model nozzle. This mechanically realizes the opening and closing of the jet flow, which has a fast response and high precision, can meet the similarity requirements, and solves the technical problem that it is difficult to simulate the model rotation and lateral jet flow at the same time in wind tunnel tests. 2. This invention achieves adjustable control of the jet flow action time and phase through the technical features of locking the air supply mandrel or swinging within a certain angle range, as well as the matching design of the air supply head slot and the model nozzle, thereby simulating the lateral jet flow action under different working conditions in the wind tunnel. 3. This invention achieves airtight connection under relative motion conditions through the sliding fit structure and sliding sealing structure between the air supply head and the model, thereby ensuring stable delivery of high-pressure gas and realizing reliable opening and closing of the jet. 4. This invention, by constructing an integrated test device that couples rotation and lateral jet flow and using corresponding test methods, realizes the synchronous simulation of projectile rotation and lateral jet flow in a wind tunnel. This allows for the acquisition of jet flow interference characteristics under different operating conditions, revealing the flow coupling mechanism between rotation and lateral jet flow, and providing experimental basis for aerodynamic layout and control system design. Attached Figure Description

[0019] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a schematic diagram of the principle of the integrated wind tunnel test device with rotation and lateral jet coupling of the present invention; Figure 2 This is a three-dimensional schematic diagram of the matching point between the air supply head and the model nozzle in an embodiment of the present invention.

[0020] The diagram shows: Detailed Implementation

[0021] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0022] like Figure 1 As shown, this embodiment of the invention provides an integrated wind tunnel testing device coupling rotation and lateral jet flow, comprising: a model 1, a balance support rod 2, an air supply mandrel 3, a roll servo motor 4, a mandrel servo motor 5, an air supply head 7, a sliding sealing ring 10, and a high-pressure gas supply channel 6. The integrated wind tunnel testing device coupling rotation and lateral jet flow provided by this invention operates on an aircraft model 1, which is fixedly connected to the balance support rod 2. The model 1 is driven to rotate around its axis by the roll servo motor 4 located at the rear of the device to simulate the roll motion of an aircraft. Specifically, the roll servo motor 4 is located at the end of the balance support rod 2 away from the model 1 and is connected to the balance support rod 2 or the test model for transmission, used to drive the model 1 to roll around its axis. Both Model 1 and Balance Support 2 are hollow structures. The air supply mandrel 3 passes through the hollow channel of Balance Support 2 and Model 1 along its axial direction, with gaps maintained between the components. These gaps are designed according to the rigidity of Model 1 and are typically no less than 1.5 mm to avoid structural interference during testing. One end of the air supply mandrel 3 is fixedly connected to the air supply head 7, and the other end is connected to the mandrel servo motor 5. The air supply mandrel 3 can swing within a limited angle range under the drive of the mandrel servo motor 5, or be in a motion-locked state. Furthermore, the air supply head 7 has an air supply head slot 8; a model nozzle 9 is provided at a corresponding position on Model 1. The dimensions of the model nozzle 9 within its throat diameter match the air supply head slot 8, while the portion outside the throat diameter is used to simulate the structure of a real lateral jet nozzle. Specifically, a sliding fit structure is formed between the model nozzle 9 and the air supply head 7, and the airtightness around the air supply head slot 8 is ensured by the sliding sealing ring 10. A high-pressure gas supply channel 6 is located at one end of the balance support rod 2 and is connected to the gas supply mandrel 3 to form a gas supply path for high-pressure gas to be delivered to the gas supply head 7 via the gas supply mandrel 3. More specifically, the aforementioned sliding sealing ring 10 is circular and is installed on both sides of the slotted hole of the gas supply head 7. Through sliding friction, it cooperates with the model nozzle 9 to form a cylindrical sealed space, reducing the leakage of gas flowing out of the slotted hole of the gas supply head 7 to both ends. The pressure of the high-pressure gas in this invention is determined by the test requirements, typically between 1 MPa and 10 MPa.

[0023] Furthermore, the working principle of this invention is as follows: Driven by the rolling servo motor 4, the model 1 rotates around its axis, causing the relative position of the model nozzle 9 and the slotted air supply head 8 to change periodically, thereby achieving periodic on / off switching of high-pressure gas. The high-pressure gas is sequentially transmitted along the high-pressure gas supply channel 6 to the air supply mandrel 3 to the air supply head 7, forming a continuous air supply path, and is ejected from the model nozzle 9 to simulate the effect of a lateral jet. Simultaneously, driven by the mandrel servo motor 5, the air supply mandrel 3 can swing within a certain angle range, thereby adjusting the fan-shaped range of a single jet effect. That is, through the structural design of the air supply head 7 and the model nozzle 9, this invention ensures that the jet is only conducted during the specified rolling phase of the model 1, forming a periodic on / off instantaneous jet effect, matching the requirements of actual working conditions.

[0024] Furthermore, embodiments of the present invention also provide an integrated wind tunnel testing method coupling rotation and lateral jet flow, implemented using the integrated wind tunnel testing device coupling rotation and lateral jet flow provided by the present invention, comprising: Step S1: Install model 1 and the test device of the present invention; specifically, the slotted installation direction of the air supply head 7 is usually facing the plane of attack of the aircraft, upward or downward; select the number and phase of the nozzle opening of the aircraft model 1 according to the test purpose, and control the state of model 1 to the initial zero position. In the above initial zero position state, the high pressure gas is in a sealed state and the jet does not work. Step S2: Start the data acquisition system, start the wind tunnel, and after the flow field inside the wind tunnel stabilizes, supply high-pressure gas. After the gas pressure stabilizes, start the test. Step S3: Control model 1 to rotate at the test speed driven by the rolling servo motor 4. Each rotation of model 1 causes the nozzles 9 of each model to spray air once. The working fan-shaped area of ​​the nozzle is determined by the slot width of the air supply head 7 and the slot width of the mating surface of the model nozzle 9. Assume the diameter of the mating surface is... The width of the slot in the air supply head 7 The width of the groove on the mating surface of the nozzle 9 of the model Model 1 rotational speed is When the spindle is locked, the angle of the jet working sector is... for:

[0025] Jet working time for:

[0026] Adjust the size of the jet's working sector area, and control the jet's effective range within the air supply spindle 3 at a rotational speed of [missing information]. Rotate, rotation angle is Then the angle of the jet working sector The adjustment is now as follows: ; Step S4: After stabilizing and collecting data from multiple cycles of experiments, stop the experiment; specifically, the order of stopping the experiment is as follows: Step S41: Control the rotational speed of Model 1 to zero; Step S42: Shut down the high-pressure gas; Step S43: Stop the wind tunnel; Step S44: Stop data acquisition.

[0027] The present invention will now be further described with reference to a more specific embodiment, in which: An integrated wind tunnel test device coupling rotation and lateral jet flow was constructed, comprising a model 1, a balance support rod 2, a gas supply mandrel 3, a gas supply head 7, a sliding sealing ring 10, a rolling servo motor 4, a mandrel servo motor 5, and a high-pressure gas supply channel 6. Model 1 is fixedly connected to the balance support rod 2 and driven by the rolling servo motor 4 located at the rear of the device, achieving controllable rotation around its axis to simulate the rolling motion of a projectile. Both model 1 and the balance support rod 2 are hollow structures. The gas supply mandrel 3 passes through the hollow channels inside model 1 and balance support rod 2 along the axial direction, with a gap between it and the inner wall to avoid structural interference during the test. One end of the gas supply mandrel 3 is fixedly connected to the gas supply head 7, and the other end is connected to the mandrel servo motor 5. The gas supply mandrel 3 can be in a rolled locked state or swing within a limited angle range under the drive of the mandrel servo motor 5. High-pressure gas enters the interior of the gas supply mandrel 3 through the gas supply channel 6 and is delivered to the internal cavity of the gas supply head 7. The side of the air supply head 7 has a square air supply head slot 8 machined within a preset fan-shaped angle range, through which high-pressure gas can be released. A model nozzle 9 is machined at a corresponding position on the model 1. The dimensions of the model nozzle 9 within its throat diameter match the air supply head slot 8, while the portion beyond the throat diameter is used to simulate the structure of a real lateral jet nozzle. A sliding fit structure is formed between the model nozzle 9 and the air supply head 7, and the airtightness around the air supply head slot 8 is maintained by the sliding sealing ring 10, thereby achieving periodic switching between a "sealed state" and a "conducting state" during relative movement.

[0028] Furthermore, the test method for the integrated wind tunnel test device based on the rotation and lateral jet coupling of this embodiment is as follows: During the test preparation phase, model 1 and its components are installed, and the installation direction of the air supply head slot 8 is set according to the test requirements, typically facing the plane of attack (upward or downward). The number of openings and their phase distribution of the model nozzle 9 are selected according to the test objective, and model 1 is adjusted to its initial zero position. At this point, the air supply head slot 8 and the model nozzle 9 are not aligned, the high-pressure gas is sealed, and the jet is not working. During the test operation phase, the data acquisition system and wind tunnel equipment are started sequentially. Once the flow field reaches a stable state, the high-pressure gas supply is turned on, and the formal test begins after the supply pressure stabilizes. Model 1 is rotated at a set speed r by a rolling servo motor 4. During rotation, the relative position between the air supply head slot 8 and the model nozzle 9 changes periodically, thus achieving periodic on / off switching of the high-pressure gas. Whenever they align, the high-pressure gas is ejected through the model nozzle 9, forming a lateral jet effect. The spatial range of the jet effect is determined by the geometric dimensions of the mating area between the air supply head slot 8 and the model nozzle 9. Let the diameter of the model nozzle mating surface be d, the slot width of the air supply head be a1, and the slot width of the model nozzle mating surface be a2. Then, when the air supply mandrel 3 is locked in place, the working sector of the jet flow is: [Missing information - likely a diameter value]. The width of the slot in the air supply head 7 The width of the groove on the mating surface of the nozzle 9 of the model Model 1 rotational speed is When the air supply spindle 3 is locked, the angle of the jet working sector is... for:

[0029] Jet working time for:

[0030] Adjust the size of the jet's working sector area, and control the jet's effective range within the air supply spindle 3 at a rotational speed of [missing information]. Rotate, rotation angle is Then the angle of the jet working sector The adjustment is now as follows:

[0031] This enables active control over the jet's action time and phase, improving the coverage of test conditions.

[0032] At the end of the experiment, after stabilizing and collecting data from multiple cycles, the following steps were executed in sequence: first, the model rotation speed was reduced to zero; then, the high-pressure gas supply was shut off; then, the wind tunnel operation was stopped; finally, the data acquisition system was stopped, and the experiment was completed.

[0033] Furthermore, in terms of experimental parameter design, the technical solution provided by this invention, in addition to conventional parameters such as Mach number, angle of attack, rotational speed, and jet pressure ratio, can also change the jet working time by adjusting the size of the jet's working fan, and can also simulate the sequential operation of multiple nozzles; specifically... Jet working time for:

[0034] in, Indicates the working fan of the jet stream. This indicates the model's rotational speed.

[0035] In summary, this invention provides an integrated wind tunnel testing device and method for coupling rotation and lateral jet flow. The device includes a test model 1, a balance support rod 2, a gas supply mandrel 3, a gas supply head 7, a sliding sealing ring 10, a rolling servo motor 4, a mandrel servo motor 5, and a high-pressure gas supply channel 6. The test model 1 is fixedly connected to the balance support rod 2 and can rotate under the drive of the rolling servo motor 4. The gas supply mandrel 3 passes through the mandrel 1 and supplies high-pressure gas to the gas supply head 7. The gas supply head 7 and the model nozzle 9 form a sliding fit, and the periodic opening and closing of the jet flow is achieved by changing the relative position. The range and duration of the jet flow can be adjusted by swinging the gas supply mandrel 3.

[0036] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0037] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. An integrated wind tunnel testing device coupling rotation and lateral jet flow, characterized in that, include: Test model (1), balance support rod (2), air supply mandrel (3), rolling servo motor (4), mandrel servo motor (5), high-pressure gas supply channel (6) and air supply head (7); The test model (1) is fixedly connected to the balance support rod (2); The rolling servo motor (4) is connected to the balance support rod (2) for transmission, and is used to drive the test model (1) and the balance support rod (2) to roll around the axis; The test model (1) and the balance support rod (2) are both hollow structures. The air supply spindle (3) passes through the hollow channel of the test model (1) and the balance support rod (2) along the axis of the hollow structure. One end of the air supply spindle (3) is fixedly connected to the air supply head (7), and the other end is connected to the spindle servo motor (5). The spindle servo motor (5) is used to drive the air supply spindle (3) to lock or swing within a limited angle. The air supply head (7) has an air supply head slot (8), and the test model (1) has a model nozzle (9) corresponding to the position of the air supply head slot (8). The high-pressure gas supply channel (6) is connected to the gas supply spindle (3) to form a high-pressure gas delivery path; when the test model (1) rolls, the relative position of the model nozzle (9) and the gas supply head slot (8) changes periodically to realize the periodic opening and closing of the jet flow, and the gas supply spindle (3) swings to adjust the range and time of the jet flow. The high-pressure gas supply channel (6) delivers high-pressure gas at a pressure of 1 MPa to 10 MPa.

2. The integrated wind tunnel testing device with rotational and lateral jet coupling according to claim 1, characterized in that, It also includes multiple sets of sliding seals (10); The sliding sealing ring (10) is set between the air supply head (7) and the model nozzle (9) to achieve an airtight seal around the slot (8) of the air supply head.

3. The integrated wind tunnel testing device with rotational and lateral jet coupling according to claim 2, characterized in that, The sliding sealing ring (10) is annular, and there are two of them. They are installed on both sides of the opening of the air supply head slot (8) between the air supply head () and the model nozzle () wall, and slide and rub against the model nozzle (9) to form a cylindrical sealing space.

4. The integrated wind tunnel testing device with rotational and lateral jet coupling according to claim 1, characterized in that, The dimensions within the throat diameter of the model nozzle (9) are matched with the slot of the air supply head (8).

5. The integrated wind tunnel testing device with rotational and lateral jet coupling according to claim 1, characterized in that, The gap between the air supply mandrel (3) and the hollow inner wall of the test model (1) and the balance support rod (2) is not less than 1.5 mm.

6. An integrated wind tunnel testing method coupling rotation and lateral jet flow, characterized in that, This is achieved using an integrated wind tunnel testing apparatus with rotational and lateral jet coupling as described in any one of claims 1 to 5, comprising: Step S1: Install the test model (1) and the test device, and adjust the test model (1) to the initial zero position. At this time, the high-pressure gas is sealed and the jet is closed. Step S2: Start the data acquisition system and wind tunnel, and turn on the high-pressure gas supply after the flow field stabilizes; Step S3: Drive the test model (1) to rotate by the rolling servo motor (4), and periodically align the model nozzle (9) with the air supply head slot (8) to achieve periodic on and off of the jet flow; adjust the swing angle of the air supply spindle (3) by the spindle servo motor (5) to adjust the working fan of the jet flow and the working time. Step S4: After collecting data from multiple cycles of the experiment, stop the experiment.

7. The integrated wind tunnel testing method for rotational and lateral jet coupling according to claim 6, characterized in that, In step S1, the installation direction of the air supply head slot (8) is directly opposite the plane of attack of the aircraft.

8. The test method according to claim 6, characterized in that, In step S3: The control model (1) rotates under the drive of the rolling servo motor (4) at the test speed. Each time the model (1) rotates once, the nozzles of each model nozzle (9) spray once. The working sector shape of the nozzle is determined by the slot width of the air supply head (7) and the slot width of the nozzle mating surface of the model nozzle (9). Assuming the diameter of the mating surface is... The slot width of the air supply head (7) The groove width of the nozzle mating surface of the model nozzle (9) Model (1) has a rotational speed of When the air supply spindle (3) is locked, the angle of the jet working sector is... for: Jet working time for: Adjust the size of the jet working sector area and control the rotation speed of the air supply spindle (3) within the jet action range. Rotate, rotation angle is Then the angle of the jet working sector The adjustment is now as follows: 。 9. The test method according to claim 6, characterized in that, In step S4, the steps to stop the test operation include: Step S41: Control the rotational speed of model (1) to zero; Step S42: Shut down the high-pressure gas; Step S43: Stop the wind tunnel; Step S44: Stop data acquisition.

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