Wind tunnel boundary layer control mechanism and supersonic wind tunnel
A control mechanism and boundary layer technology, which is applied in the direction of machine/structural component testing, measuring devices, instruments, etc., can solve the problem of the effective test area of the wind tunnel test section becoming smaller, so as to increase the effective test area, reduce the impact, The effect of speeding up the flow
Active Publication Date: 2020-06-12
INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI +1
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[0003] However, there are large velocity gradients and vortices in existing wind tunnels, especially in the boundary layer of supersonic wind tunnels, and their viscosity has a great influence on the flow of wind tunnels, which makes the effective test area of the wind tunnel test section change. Small
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Embodiment 1
[0034] For the supersonic wind tunnel using the above results, the specific size parameters are designed as follows: image 3 As shown, the initial inclination angle θ 1 Set to 34°, the maximum central body angle θ 2 Set to 21°; the radial distance between the rear end of the oblique line section 511 and the first bottom edge 512 is less than or equal to 1 / 25 of the inner wall radius of the test section 4; The maximum radial spacing point between the first bases 512 is used as the apex of the first arc segment 513, and the radial distance between the apex and the second base 521 is the apex and the first base 2 / 3 of the radial spacing of 512; the radial spacing between the second bottom edge 521 and the second top edge 522 serves as the radial thickness of the lip cover ring 52, and the radial thickness of the lip cover ring 52 The thickness remains consistent, and is 1 / 3 of the radial distance between the rear end of the oblique segment 511 and the first bottom edge 512; ta...
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The invention discloses a wind tunnel boundary layer control mechanism and a supersonic wind tunnel. The wind tunnel boundary layer control mechanism comprises a convex ring piece fixedly installed onthe inner wall of a wind tunnel test section, a lip mask ring piece in the convex ring piece in a sleeving manner, a connecting rod for connecting the convex ring piece and the lip mask ring piece; the central axes of the test section, the convex ring piece and the lip mask ring piece are coaxially arranged; the outer ring surface of the lip mask ring piece, the inner ring surface of the lip maskring piece and the inner ring surface of the convex ring piece are curved surfaces which protrude towards the direction close to the central axis of the convex ring piece; a gap is formed between theouter ring surface of the lip mask ring piece and the inner ring surface of the convex ring piece to form an annular airflow channel; the axial section area of the annular airflow channel is kept unchanged, the gap between the outer ring face of the lip cover ring piece and the inner ring face of the convex ring piece is gradually decreased in the air inlet direction of the wind tunnel, the position close to a wind tunnel air inlet serves as the front, the position away from the air inlet serves as the rear, and the front end of the convex ring piece is located in front of the front end of the lip cover ring piece. The influence of a boundary layer on a wind tunnel test section can be reduced, and the effective test area of the test section is increased.
Description
technical field [0001] The invention belongs to the technical field of aero-engine testing, and in particular relates to a wind tunnel boundary layer control mechanism and a supersonic wind tunnel. Background technique [0002] The aerodynamic test is a necessary means to verify the performance of the aircraft. Due to the complexity of the gas flow phenomenon and the geometric shape of the aircraft, it is necessary to go through a large number of experiments to find out its laws and then combine with theoretical analysis to obtain its performance. The wind tunnel is a basic equipment for aerodynamic tests. It is a pipeline system designed according to certain requirements. It can use the power drive device to generate controllable airflow, and then conduct the airflow field according to the principle of relativity and similarity of object motion. Test equipment. [0003] However, there are large velocity gradients and vortices in existing wind tunnels, especially in the bo...
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IPC IPC(8): G01M9/02G01M9/04
CPCG01M9/02G01M9/04
Inventor 李庆海阮昌龙王月李富才郭玉超李德彬于磊辉王勋
Owner INST OF ENGINEERING THERMOPHYSICS - CHINESE ACAD OF SCI