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

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...

AI Technical Summary

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

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