Observation method of hypersonic internal flow-field wave structure

Abstract

The invention discloses an observation method of a hypersonic internal flow-field wave structure, particularly a method for obtaining a model internal flow-field wave structure, which is simple, feasible, and low in construction cost. The observation method utilizes theories of glow discharge flow-field display technologies to carry out partial cross-section observation on the model internal flow-field wave structure. In a test, one side of a model is made of a transparent material, so that glow discharge images are shot conveniently; a plurality of discharge electrodes are arranged on internal relative walls of the model, a discharge control unit is adopted for selecting a pair of the electrodes in sequence to discharge, and a synchronous control unit is adopted for synchronizing glow discharge and camera shooting, therefore, flow-field wave structures of multiple sections can be obtained in one test. The method has the advantages of simple structure and relatively low equipment requirements, and is a flow-field display method which can be used in hypersonic low-density wind tunnels.

Description

technical field [0001] The invention relates to a method for observing the wave system structure of a hypersonic internal flow field, which belongs to the field of wind tunnel flow field display. Background technique [0002] In conventional hypersonic wind tunnel tests, the schlieren method or the shadow method are generally used to display the wave system structure of the flow field around the model, but both the schlieren and shadow methods are based on the fact that the optical refractive index of the gas is a function of density. It is measured by the principle of light deflection. Since optical refraction is an integral process of a path, it is impossible to use the above two methods to observe the wave system structure of the flow field in the model, let alone to carry out the wave system structure of the flow field at different positions in the model. observe. Contents of the invention [0003] The technical problem to be solved by the present invention is to prov...

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Problems solved by technology

[0002] In conventional hypersonic wind tunnel tests, the schlieren method or the shadow method are generally used to display the wave system structure of the flow field around the model, but both the schlieren and shadow methods are based on the fact that the optical refractive index of the gas is a function of density. It is measured by the principle of light deflection. Since optical refraction is an integral process of a path, it is impossible to use the above two methods to observe the wave system structure of the flow field in the model, let alone to carry out the wave system structure of the flow field at different positions in the model. to observe

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