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A method for obtaining pressure matching points of supersonic jet dynamic operation in jet wind tunnel

A matching point and jet flow technology, applied in aerodynamic tests, machine/structural component testing, instruments, etc., can solve problems such as limiting high-speed free jet flow in wind tunnels, reduce the number of start-ups in wind tunnels, simplify ideas, and save energy The effect of consumption

Active Publication Date: 2022-07-19
INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

[0004] The significant advantage of the high-speed free-jet wind tunnel is that the blockage of the model is allowed to be large, but the uniform area of ​​the supersonic jet flow field under the traditional operation mode is small, which limits the role of the high-speed free-jet wind tunnel
The static pressure matching point method can only adapt to the situation where the model state remains unchanged or changes slightly. Once the model state changes greatly, the matching pressure of the flow field needs to be changed accordingly to maintain a large uniform area in the supersonic flow field. scope

Method used

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  • A method for obtaining pressure matching points of supersonic jet dynamic operation in jet wind tunnel
  • A method for obtaining pressure matching points of supersonic jet dynamic operation in jet wind tunnel
  • A method for obtaining pressure matching points of supersonic jet dynamic operation in jet wind tunnel

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Embodiment 1

[0045] like figure 2 As shown, according to the airflow direction of the wind tunnel, from front to back are the nozzle, test chamber 4 and collector 5 of the high-speed free jet wind tunnel. Supersonic nozzle Mach number 2.0; static pressure matching point , the dynamic operating pressure matching accuracy a=100%, b=2%; the model is as follows image 3 Cross total pressure bracket shown.

[0046] In this example, the cross total pressure bracket is used for measurement, and the static pressure matching conditions (the total pressure of the fixed and stable section) are used. ) and the uniformity change of the flow field under dynamic pressure matching conditions (total pressure changes according to the matching conditions) as a comparison, the moving measurement process of the cross total pressure bent in the wind tunnel simulates the state change process of the model in the wind tunnel, See the schematic diagram of the moving measurement of the cross total pressure ben...

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Abstract

The invention belongs to the technical field of high-speed free jet wind tunnel testing, and discloses a method for obtaining a dynamic operating pressure matching point of a supersonic jet in a jet wind tunnel. The method includes the following steps: arranging static pressure measuring points in the high-speed free jet wind tunnel; installing a model on the moving measuring mechanism of the high-speed free jet wind tunnel, and the model is at the initial state position; starting the high-speed free jet wind tunnel; continuously adjusting the pressure regulating valve Open, after stabilization, collect the data of the model at the initial state position; transform the model to the second state, and collect the data of the second state of the model after stabilization; continue to change the model state until all data is collected; close the high-speed free jet wind tunnel . The method for obtaining the dynamic operating pressure matching point of supersonic jet in the jet wind tunnel of the present invention has a simple and clear idea, and has sufficient theoretical basis, which is helpful to accurately obtain the corresponding operating pressure matching point under the condition of the state change of the test model, and takes into account the uniformity of the flow field and the Test quality efficiency requirements.

Description

technical field [0001] The invention belongs to the technical field of high-speed free jet wind tunnel test, and particularly relates to a method for obtaining a pressure matching point of supersonic jet dynamic operation in a jet wind tunnel. Background technique [0002] In traditional high-speed free-jet wind tunnels, when conducting supersonic tests, air is usually carried out by increasing the total operating pressure, which can ensure uniform airflow at the rhombus-shaped area at the nozzle outlet. However, the air flow will undergo repeated expansion acceleration and compression deceleration processes outside the diamond-shaped area and within the jet boundary, resulting in a sharp deterioration of the flow field quality outside the diamond-shaped area. The uniform airflow within the diamond-shaped area can be tested for small-angle-of-attack intake ports, engine characteristics, etc., which require a smaller range of the uniform area, and the model size cannot exceed...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01M9/02G01M9/06
CPCG01M9/02G01M9/06
Inventor 林学东罗太元尹疆祖孝勇熊能高川凌忠伟韩新峰田嘉懿刘为杰黄昊宇吴琦夏语
Owner INST OF HIGH SPEED AERODYNAMICS OF CHINA AERODYNAMICS RES & DEV CENT
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