Ejector-driven closed-loop recirculation temporary impulse supersonic wind tunnel flow field control method

Abstract

The invention discloses an ejector-driven closed-loop recirculation temporary impulse supersonic wind tunnel flow field control method. An ejector arranged behind a diffusion section is adopted as themain drive of a wind tunnel flow field, under the cooperation of a recirculation regulating valve, an assisting air admission pressure regulating valve and an exhaust throttle valve, a stable supersonic flow field is established, wherein precise control of the total pressure of a stabilizing section is achieved under the mutual action of a pressure regulating valve of the ejector and the assisting air admission pressure regulating valve, and on the basis of the precise control of the total pressure, the establishing of stable supersonic flow fields with different M values under the same operation total pressure in a temporary impulse supersonic wind tunnel can be achieved under the cooperation of a nozzle profile surface and a diffusion section profile surface. By means of the method, thesimulation of negative pressure working conditions can be achieved in a closed-loop recirculation temporary impulse supersonic wind tunnel, the operating envelope and simulation range of the wind tunnel are effectively expanded, and the total pressure of a stabilizing section needed by the establishing of a supersonic flow field when the M value of a traditional temporary impulse wind tunnel is high can be significantly reduced, which facilitates the aerodynamic loading of a model and the improvement of the measuring accuracy of a strain gauge balance of the wind tunnel.

Description

technical field [0001] The invention relates to the field of flow field control of a temporary supersonic wind tunnel, in particular to a method for controlling the flow field of a semi-return temporary supersonic wind tunnel for an ejector system and an exhaust throttling system. Background technique [0002] A wind tunnel is a pipeline-shaped ground test simulation device that can artificially generate and control airflow to simulate the flow of air around an aircraft or object, measure the effect of airflow on an object, and observe physical phenomena. According to the simulation speed, wind tunnels are divided into low-speed wind tunnels (M≤0.4), high-speed wind tunnels (0.4<M≤4.5) and hypersonic wind tunnels (M≥5.0). In the high-speed wind tunnel, it is divided into sub-transonic wind tunnel (M=0.4~1.4) and supersonic wind tunnel (M=1.5~4.5). The wind tunnel simulates the corresponding M number by controlling the pressure ratio of the airflow in the wind tunnel duct...

AI Technical Summary

Problems solved by technology

[0005] The object of the present invention is to provide a temporary supersonic wind tunnel with closed-loop backflow driven by ejection, aiming at the problem that a stable supersonic flow field with different M numbers cannot be established under the same total pressure in the closed-loop backflow temporary supersonic wind tunnel. Cave Flow Field Control Method

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