Conventional and high angle of attack and high sideslip angle inlet test device and method in temporary wind tunnel

Abstract

The present invention belongs to the technical field of wind tunnel test, and discloses a test device and method for conventional and high angle of attack and high sideslip angle inlet ducts in a temporary wind tunnel. The upper back surface of the tail of the inlet duct model of the test device is connected to the model connection block, the side-slip front axle, the main bracket and the scimitar of the temporary wind tunnel scimitar mechanism from front to back in sequence, and the lower abdomen air outlet of the tail is connected to the medium-pressure hose adapter section, the medium-pressure hose, the telescopic sleeve, the flow meter and the ejector in sequence from front to back. The test method includes wind tunnel test preparation; carrying out conventional inlet duct tests; carrying out high angle of attack and high sideslip angle inlet duct tests; and test data processing. The test device and method adopt the method of "close-range" pre-deflection of the angle of attack and "secondary" deflection of the sideslip angle to ensure that the inlet duct model is always in the core flow field of the wind tunnel test section; the telescopic sleeve adopts a "double-layer opposite side" sealing design to form a "damping" cavity pressure to suppress the shaking of the medium-pressure hose; the efficiency of the inlet duct test, the accuracy of the data and the versatility of the test system are improved.

Description

Technical Field

[0001] The invention belongs to the technical field of wind tunnel testing, and in particular relates to a temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device and method. Background Art

[0002] The air inlet is an important part of the aircraft propulsion system, and is responsible for providing high-quality air for the engine. The performance of the air inlet is directly related to the performance of the propulsion system, and even the improvement of the aircraft's technical and tactical capabilities. For most aircraft, it is necessary not only to maintain high aerodynamic performance in the cruise state, but also to have a certain degree of maneuverability. When the aircraft is flying at high maneuvers and high angles of attack, the complex flow, strong asymmetry and unsteadiness of the flow will further deteriorate the air intake environment and air intake quality, reduce the compatibility of the air inlet and the engine, and even cause engine surge or shutdown. When a multi-engine aircraft is flying at high maneuvers and high angles of attack, the air inlets may interfere with each other, and the high angle of attack characteristics of the multi-engine air inlets must be simulated and studied at the same time. For fighters, the requirements for cruise performance and high angle of attack maneuverability are very high.

[0003] Wind tunnel test is the most direct and reliable technical means to obtain the characteristics of aircraft inlet, and can quickly, systematically and scientifically obtain the performance parameters of aircraft inlet. At present, the temporary impulse type is the conventional form of high-speed wind tunnel. Its principle is to introduce the high-pressure gas in the gas tank into the wind tunnel pipe and rectify it, and then establish a uniform flow field with a certain flow velocity in the test section. Through the model and test system installed in the test section, the flight environment of the aircraft in the sky is simulated and the relevant design parameters are obtained. The temporary impulse wind tunnel will bring huge impact when starting and shutting down. Therefore, the design requirements for the temporary impulse wind tunnel model support system are relatively high; in order to improve the structural strength, except for the high angle of attack aerodynamic characteristics test and CTS test (the missile model size is relatively small), due to the influence of motor drive power and other aspects, most of the test models of the temporary impulse wind tunnel generally adopt pre-biased design for high angle of attack, conventional sideslip angle and large sideslip angle.

[0004] At present, most high angle of attack and high sideslip inlet tests are generally carried out in 2-meter transonic wind tunnels, which are limited by the size of the wind tunnel. In high angle of attack inlet tests, in order to ensure a certain structural strength, it is often achieved by replacing the pre-biased struts. The replacement of the pre-biased struts often requires the model and the pre-biased struts to be disassembled and reassembled; because the model is heavy, the test pipeline is more complicated, and the entire disassembly and assembly process takes a long time. The sideslip angle of the inlet is achieved by lateral pre-biasing of the support system components. The shaft position is usually selected near the scimitar or the head of the main bracket. This single side-slip pre-biasing method often causes the model to deviate from the core flow field area of ​​the wind tunnel test section after the side-slip pre-biasing, especially after the large side-slip pre-biasing, the model head and the inlet inlet are very close to the wind tunnel wall, which has a great impact on the accuracy of the test results. At the same time, after the pre-biasing of the inlet model angle of attack and sideslip angle, it will also cause a significant change in the length of the inlet outlet airflow pipeline. At present, the method adopted is mainly to replace medium-pressure hoses of different lengths. The inlet test, which includes conventional and high angle of attack and high sideslip tests, is relatively complex and has low test efficiency. Especially in some transient wind tunnels, the support systems for conventional angle of attack and sideslip tests and high angle of attack and high sideslip tests are two sets of systems, which requires huge workload for test preparation and support system replacement.

[0005] Therefore, how to optimize the angle of attack, sideslip angle pre-bias and pipeline design of the inlet test device is a key issue faced by the temporary wind tunnel inlet test device. It mainly includes three aspects: first, how to simplify the angle of attack pre-bias process, reduce the replacement time, and improve the efficiency of the inlet test; second, to ensure that after the sideslip angle pre-bias, the inlet model is always in the core flow field area of ​​the wind tunnel test section to improve the reliability of the test data; third, the length of the airflow pipeline is adjustable to meet the needs of different types of tests and different angles of attack and sideslip angles.

[0006] Currently, there is an urgent need to develop a temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device and method. Summary of the invention

[0007] One technical problem to be solved by the present invention is to provide a temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device. Another technical problem to be solved by the present invention is to provide a temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test method, which is used for the angle of attack, sideslip angle pre-bias and pipeline design of the inlet test device to overcome the defects of the prior art.

[0008] The upper back of the tail of the inlet model of the conventional and high angle of attack and high sideslip angle inlet test device of the temporary wind tunnel of the present invention is connected in sequence from front to back to the model connection block, the side slip front axle, the main bracket and the scimitar of the temporary wind tunnel scimitar mechanism; the lower abdomen air outlet of the tail of the inlet model is connected in sequence from front to back to the medium pressure hose adapter section, the medium pressure hose, the telescopic sleeve, the flow meter and the ejector, and the outlet airflow of the inlet model flows into the mainstream of the temporary wind tunnel through the medium pressure hose adapter section, the medium pressure hose, the telescopic sleeve, the flow meter and the ejector;

[0009] The model connection block and the sideslip front axis are connected through a pitch rotation axis in the left and right directions. The model connection block and the sideslip front axis are matched through an arc surface I along the central axis direction of the pitch rotation axis according to the right-hand rule. The contact surface of the arc surface I is positioned and connected by pins distributed equidistantly according to the circumference and screws. The model connection block and the sideslip front axis rotate relatively around the pitch rotation axis to change the pre-bias angle of the inlet model.

[0010] The sideslip front axle and the front section of the main bracket are connected by the sideslip front rotating shaft in the up-down direction, and the sideslip front axle and the front section of the main bracket are matched by arc surface II along the central axis direction of the sideslip front rotating shaft according to the right-hand rule; the sideslip front axle and the main bracket rotate relatively around the sideslip front rotating shaft, and the relative sideslip angle I is fixed by the front sideslip angle changing block on the contact surface of the arc surface II, and the front sideslip angle changing block is positioned by pins and connected and fixed by screws;

[0011] The rear section of the main bracket and the scimitar of the temporary wind tunnel scimitar mechanism are connected through the sideslip rear rotating shaft in the up and down directions. The rear section of the main bracket and the scimitar of the temporary wind tunnel scimitar mechanism are matched through arc surface III along the central axis direction of the sideslip rear rotating shaft according to the right-hand rule. The sideslip front shaft and the main bracket rotate relatively around the sideslip rear rotating shaft. The relative sideslip angle II is fixed on the contact surface of the arc surface III by the rear sideslip angle variable block. The rear sideslip angle variable block is positioned by pins and fixed by screws. The relative sideslip angle I and the relative sideslip angle II are superimposed to obtain the sideslip angle of the inlet model.

[0012] Furthermore, it is characterized in that the scimitar of the temporary wind tunnel scimitar mechanism is divided into an upper scimitar and a lower scimitar; the lower end of the upper scimitar is connected to the upper connecting ear, and the upper end of the lower scimitar is connected to the lower connecting ear, and the rear rotating shaft is located inside the upper connecting ear and the lower connecting ear after sliding sideways, and the upper connecting ear and the lower connecting ear are connected in series up and down.

[0013] Furthermore, the telescopic sleeve is a double-layer sleeve with inner and outer layers nested, and sealing rings are respectively arranged on the outer surface of the inner sleeve and the inner surface of the outer sleeve.

[0014] Furthermore, the front side sliding angle block and the rear side sliding angle block both adopt partial spline gears.

[0015] The method for testing conventional and high angle of attack and high sideslip angle inlet in a temporary wind tunnel of the present invention comprises the following steps:

[0016] S10. Wind tunnel test preparation;

[0017] Install the temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test equipment in the temporary wind tunnel, and adjust the attitude of the inlet model to the initial angle of attack and initial sideslip angle;

[0018] S20. Carry out routine air intake tests;

[0019] Start the wind tunnel and establish a stable flow field; adjust and measure the airflow of the inlet model through the flow meter, and increase the airflow simulation range of the inlet model through the ejector; after the test, close the wind tunnel;

[0020] S30. Conduct high angle of attack and high sideslip angle inlet tests;

[0021] By rotating the sideslip front axis around the pitch axis, the angle of attack pre-bias of the inlet model is changed;

[0022] By rotating the main support around the sideslip rear axis and the sideslip front axis around the sideslip front axis, the sideslip angle of the air inlet model is changed, and the position of the air inlet model in the wind tunnel test section is adjusted;

[0023] The outlet airflow of the inlet model is adjusted and measured by the flow meter, and the outlet airflow simulation range of the inlet model is increased by the ejector; according to the test plan, the wind tunnel flow field speed and the angle of attack and sideslip angle of the inlet model are adjusted to complete the measurement of the inlet performance data under all test conditions;

[0024] After the test, the wind tunnel was closed;

[0025] S40. Experimental data processing;

[0026] According to the test data format requirements, the test data is processed to obtain the intake duct performance data of the intake duct model.

[0027] The temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device and method of the present invention have the following characteristics:

[0028] 1. The “close-range” pre-bias of the inlet model’s angle of attack is achieved through the model connection block and the sideslip front shaft; the “secondary” deflection of the inlet model’s sideslip angle is achieved through the relative sideslip angle I and relative sideslip angle II; the support system structure of the inlet model is well optimized by adopting the “close-range” pre-bias of the angle of attack and the “secondary” deflection of the sideslip angle, ensuring that the inlet model is always in the core flow field area of ​​the wind tunnel test section, thereby improving the test efficiency and data accuracy;

[0029] 2. Both the front and rear side slip angle blocks adopt the structure of partial spline gears, which makes the side slip angle pre-biasing convenient and quick;

[0030] 3. The telescopic sleeve is used to adjust the length of the airflow pipeline, with a wide adjustment range; the "double-layer opposite side" seal is used, with high reliability and stable telescopic movement;

[0031] 4. A "damping" cavity pressure is formed between the two sealing rings of the telescopic sleeve, which suppresses the shaking of the medium-pressure hose during the test and improves the reliability of the support system.

[0032] The temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device and method of the present invention adopt the method of "close-range" pre-deflection of the angle of attack and "secondary" deflection of the sideslip angle, so that the structure of the inlet support system is well optimized, ensuring that the inlet model is always in the core flow field area of ​​the wind tunnel test section after the sideslip angle pre-deflection, thereby improving the test efficiency and data accuracy; the telescopic sleeve adopts a "double-layer opposite side" sealing design, which has high reliability and smooth telescopic extension, and during the telescopic process, it forms a "damping" cavity pressure, which suppresses the shaking of the medium-pressure hose during the test; the telescopic sleeve is adjustable in length and has a wide range of applications, thereby improving the inlet test efficiency, data accuracy and the versatility of the test system. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic structural diagram of the conventional and high angle of attack and high sideslip angle inlet test devices of the temporary wind tunnel of the present invention;

[0034] Figure 2 It is a partial enlarged view of A of the conventional and high angle of attack and high sideslip angle inlet test device of the temporary wind tunnel of the present invention;

[0035] Figure 3 It is a partial enlarged view of B of the conventional and high angle of attack and high sideslip angle inlet test device of the temporary wind tunnel of the present invention;

[0036] Figure 4 It is a partial enlarged view of C of the conventional and high angle of attack and high sideslip angle inlet test device of the temporary wind tunnel of the present invention.

[0037] In the figure, 1. air inlet model; 2. model connecting block; 3. sideslip front axle; 4. medium-pressure hose adapter section; 5. sideslip front rotating shaft; 6. medium-pressure hose; 7. front sideslip angle changing block; 8. telescopic sleeve; 9. main bracket; 10. flow meter; 11. ejector; 12. upper connecting ear; 13. lower connecting ear; 14. upper scimitar; 15. lower scimitar; 16. rear sideslip angle changing block; 17. inner sleeve; 18. outer sleeve. DETAILED DESCRIPTION

[0038] The present invention will be further described below in conjunction with the accompanying drawings.

[0039] Embodiment: The contact surface of the arc surface Ⅰ of this embodiment is arranged with pin positioning and screw connection which are evenly distributed at 40° circumference. The angle of attack of the air inlet model 1 can be pre-biased at an integer multiple of 40°. Combined with the aerodynamic loads of most aircraft and the strength design of the supporting structure, this embodiment can achieve an angle of attack pre-bias of 80°. At the same time, the angle of attack range of the temporary wind tunnel scimitar mechanism of this embodiment is -20°~20°, and the test angle of attack range of the air inlet model 1 can reach -20°~100°, which can meet the current conventional and large angle of attack test requirements of aircraft.

[0040] The front sideslip angle-changing block 7 and the rear sideslip angle-changing block 16 both adopt a local spline gear structure, with the angle between the inner teeth being 4° and the angle between the outer teeth being 3°; any sideslip angle within a certain sideslip range can be achieved through different deflection combinations; if a sideslip angle of 1° needs to be achieved, the main bracket 9 can be deflected by one tooth on the inner side and the outer side of the sideslip front axle 3 can be deflected by one tooth in the opposite direction. Through the “secondary” deflection of the sideslip angle, the lateral position of the inlet duct model 1 in the wind tunnel test section can be adjusted to ensure that the inlet duct model 1 is always in the core flow field area of ​​the temporary wind tunnel test section after the sideslip angle pre-deflection; for example, in order to achieve a sideslip angle of 20° for the inlet duct model 1, a pre-deflection of -10° sideslip angle is set between the main bracket 9 and the upper connecting ear piece 12 and the lower connecting ear piece 13, and a 30° sideslip angle is deflected between the sideslip front axle 3 and the main bracket 9. The lateral position of the “secondary” deflection can be basically offset, and the inlet duct model 1 is always in the core flow field area of ​​the wind tunnel test section.

[0041] like Figure 1~Figure 4 As shown, the upper back of the tail of the inlet model 1 of the conventional and high angle of attack and high sideslip angle inlet test device of the temporary wind tunnel of this embodiment is connected to the model connection block 2, the side slip front axle 3, the main bracket 9 and the scimitar of the temporary wind tunnel scimitar mechanism in sequence from front to back; the lower abdomen air outlet of the tail of the inlet model 1 is connected to the medium pressure hose adapter section 4, the medium pressure hose 6, the telescopic sleeve 8, the flow meter 10 and the ejector 11 in sequence from front to back, and the outlet airflow of the inlet model 1 flows into the mainstream of the temporary wind tunnel through the medium pressure hose adapter section 4, the medium pressure hose 6, the telescopic sleeve 8, the flow meter 10 and the ejector 11;

[0042] The model connection block 2 and the sideslip front axis 3 are connected through a pitch rotation axis in the left and right directions. The model connection block 2 and the sideslip front axis 3 are matched through an arc surface I along the central axis direction of the pitch rotation axis according to the right-hand rule. The contact surface of the arc surface I is positioned and connected by pins distributed equidistantly according to the circumference and screws. The model connection block 2 and the sideslip front axis 3 rotate relatively around the pitch rotation axis to change the pre-bias angle of the angle of attack of the inlet model 1.

[0043] The sideslip front axle 3 and the front section of the main bracket 9 are connected by the sideslip front rotating shaft 5 in the up-down direction, and the sideslip front axle 3 and the front section of the main bracket 9 are matched by the arc surface II along the central axis direction of the sideslip front rotating shaft 5 according to the right-hand rule; the sideslip front axle 3 and the main bracket 9 rotate relatively around the sideslip front rotating shaft 5, and the relative sideslip angle I is fixed by the front sideslip angle changing block 7 on the contact surface of the arc surface II, and the front sideslip angle changing block 7 is positioned by a pin and connected and fixed by a screw;

[0044] The rear section of the main bracket 9 and the scimitar of the temporary wind tunnel scimitar mechanism are connected by a side-slip rear rotating shaft in the up-down direction. The rear section of the main bracket 9 and the scimitar of the temporary wind tunnel scimitar mechanism are matched through an arc surface III along the central axis direction of the side-slip rear rotating shaft according to the right-hand rule. The side-slip front shaft 3 and the main bracket 9 rotate relatively around the side-slip rear rotating shaft. The relative side-slip angle II is fixed on the contact surface of the arc surface III by a rear side-slip angle changing block 16. The rear side-slip angle changing block 16 is positioned by a pin and fixed by a screw. The relative side-slip angle I and the relative side-slip angle II are superimposed to obtain the side-slip angle of the inlet duct model 1.

[0045] Furthermore, it is characterized in that the scimitars of the temporary wind tunnel scimitar mechanism are divided into an upper scimitar 14 and a lower scimitar 15; the lower end of the upper scimitar 14 is connected to the upper connecting ear 12, and the upper end of the lower scimitar 15 is connected to the lower connecting ear 13, and the rear rotating shaft after sliding sideways is located inside the upper connecting ear 12 and the lower connecting ear 13, and the upper connecting ear 12 and the lower connecting ear 13 are connected in series up and down.

[0046] Furthermore, the telescopic sleeve 8 is a double-layer sleeve with inner and outer layers nested inside and outside, and sealing rings are respectively provided on the outer surface of the inner sleeve 17 and the inner surface of the outer sleeve 18.

[0047] Furthermore, the front sliding angle block 7 and the rear sliding angle block 16 both adopt partial spline gears.

[0048] The conventional and high angle of attack and high sideslip angle inlet test methods of the transient wind tunnel of the present embodiment include the following steps:

[0049] S10. Wind tunnel test preparation;

[0050] Installing a temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device in the temporary wind tunnel, adjusting the attitude of the inlet model 1 to an initial angle of attack and an initial sideslip angle;

[0051] S20. Carry out routine air intake tests;

[0052] Start the wind tunnel to establish a stable flow field; adjust and measure the airflow rate of the inlet duct model 1 through the flow meter 10, and increase the airflow rate simulation range of the inlet duct model 1 through the ejector 11; after the test, close the wind tunnel;

[0053] S30. Conduct high angle of attack and high sideslip angle inlet tests;

[0054] By rotating the sideslip front axis 3 around the pitch axis, the pre-bias angle of the angle of attack of the air inlet model 1 is changed;

[0055] By rotating the main support 9 around the sideslip rear rotation axis and the sideslip front axis 3 around the sideslip front rotation axis 5, the sideslip angle of the air inlet model 1 is changed, and the position of the air inlet model 1 in the wind tunnel test section is adjusted;

[0056] The outlet airflow rate of the inlet duct model 1 is adjusted and measured by the flow meter 10, and the outlet airflow rate simulation range of the inlet duct model 1 is increased by the ejector 11; according to the test plan, the wind tunnel flow field speed and the angle of attack and sideslip angle of the inlet duct model 1 are adjusted to complete the measurement of the inlet duct performance data under all test conditions;

[0057] After the test, the wind tunnel was closed;

[0058] S40. Experimental data processing;

[0059] According to the test data format requirements, the test data is processed to obtain the intake duct performance data of the intake duct model 1.

[0060] Although the embodiments of the present invention have been disclosed above, they are not limited to the applications listed in the description and the embodiments, and can be fully applied to various fields suitable for the present invention. For those familiar with the art, additional improvements and modifications can be easily realized without departing from the principles of the present invention. Therefore, without departing from the general concept defined by the claims and equivalent scope, the present invention is not limited to the specific details and the illustrations shown and described here.

Claims

1. Temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device, characterized by: The upper back of the tail of the air inlet model (1) of the test device is connected to the model connection block (2), the side sliding front axle (3), the main bracket (9) and the scimitar of the temporary wind tunnel scimitar mechanism in sequence from front to back; the lower abdomen air outlet of the tail of the air inlet model (1) is connected to the medium-pressure hose adapter section (4), the medium-pressure hose (6), the telescopic sleeve (8), the flow meter (10) and the ejector (11) in sequence from front to back, and the outlet air of the air inlet model (1) flows into the main stream of the temporary wind tunnel through the medium-pressure hose adapter section (4), the medium-pressure hose (6), the telescopic sleeve (8), the flow meter (10) and the ejector (11); The model connection block (2) and the sideslip front axis (3) are connected via a pitch rotation axis in the left and right directions; the model connection block (2) and the sideslip front axis (3) are matched via an arc surface I along the central axis direction of the pitch rotation axis according to the right-hand rule; the contact surface of the arc surface I is positioned and connected by screws distributed at equal intervals along the circumference; the model connection block (2) and the sideslip front axis (3) rotate relative to each other around the pitch rotation axis to change the pre-bias angle of the angle of attack of the inlet model (1); The sideslip front axle (3) and the front section of the main bracket (9) are connected via a sideslip front rotating shaft (5) in the up-down direction; the sideslip front axle (3) and the front section of the main bracket (9) are matched via an arc surface II along the central axis direction of the sideslip front rotating shaft (5) according to the right-hand rule; the sideslip front axle (3) and the main bracket (9) rotate relative to each other around the sideslip front rotating shaft (5); a relative sideslip angle I is fixed on the contact surface of the arc surface II via a front sideslip angle changing block (7); the front sideslip angle changing block (7) is positioned by a pin and connected and fixed by a screw; The rear section of the main support (9) and the scimitar of the temporary wind tunnel scimitar mechanism are connected via a side-slip rear rotating shaft in the up-down direction. The rear section of the main support (9) and the scimitar of the temporary wind tunnel scimitar mechanism are matched via an arc surface III along the central axis direction of the side-slip rear rotating shaft according to the right-hand rule. The side-slip front shaft (3) and the main support (9) rotate relative to each other around the side-slip rear rotating shaft. The relative side-slip angle II is fixed on the contact surface of the arc surface III via a rear side-slip angle changing block (16). The rear side-slip angle changing block (16) is positioned by a pin and fixed by a screw connection. The relative side-slip angle I and the relative side-slip angle II are superimposed to obtain the side-slip angle of the air inlet model (1).

2. The temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device according to claim 1 is characterized in that: The scimitars of the temporary wind tunnel scimitar mechanism are divided into an upper scimitar (14) and a lower scimitar (15); the lower end of the upper scimitar (14) is connected to the upper connecting ear piece (12), and the upper end of the lower scimitar (15) is connected to the lower connecting ear piece (13); the side-sliding rear rotation shaft is located inside the upper connecting ear piece (12) and the lower connecting ear piece (13), and the upper connecting ear piece (12) and the lower connecting ear piece (13) are connected in series up and down.

3. The temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device according to claim 1 is characterized in that: The telescopic sleeve (8) is a double-layer sleeve with inner and outer sleeves nested inside and outside, and sealing rings are respectively provided on the outer surface of the inner sleeve (17) and the inner surface of the outer sleeve (18).

4. The temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device according to claim 1 is characterized in that: The front side sliding angle block (7) and the rear side sliding angle block (16) both use local spline gears.

5. A transient wind tunnel conventional and high angle of attack and high sideslip angle inlet test method, which is used in a transient wind tunnel conventional and high angle of attack and high sideslip angle inlet test device as described in any one of claims 1 to 4, characterized in that: The following steps are involved: S10. Wind tunnel test preparation; Installing a temporary wind tunnel conventional and high angle of attack and high sideslip angle inlet test device in the temporary wind tunnel, adjusting the attitude of the inlet model (1) to an initial angle of attack and an initial sideslip angle; S20. Carry out routine air intake tests; The wind tunnel is started to establish a stable flow field; the airflow rate of the air inlet model (1) is adjusted and measured by a flow meter (10), and the airflow rate simulation range of the air inlet model (1) is increased by an ejector (11); after the test is completed, the wind tunnel is closed; S30. Conduct high angle of attack and high sideslip angle inlet tests; By rotating the sideslip front axis (3) around the pitch axis, the angle of attack pre-bias of the air inlet model (1) is changed; By rotating the main support (9) around the sideslip rear rotation axis and the sideslip front axis (3) around the sideslip front rotation axis (5), the sideslip angle of the air inlet model (1) is changed, and the position of the air inlet model (1) in the wind tunnel test section is adjusted; The outlet airflow rate of the inlet duct model (1) is adjusted and measured by a flow meter (10), and the outlet airflow rate simulation range of the inlet duct model (1) is increased by an ejector (11); the wind tunnel flow field velocity and the angle of attack and sideslip angle of the inlet duct model (1) are adjusted according to the test plan, and the inlet duct performance data measurement under all test conditions is completed; After the test, the wind tunnel was closed; S40. Experimental data processing; According to the test data format requirements, the test data is processed to obtain the intake duct performance data of the intake duct model (1).

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