Experimental system and method for SWTBLI unsteady characteristic research

Abstract

The invention discloses an experimental system and method for SWTBLI unsteady characteristic research, the experimental system comprises an experimental test section and an ultrahigh frame frequency flow field measurement system, and the ultrahigh frame frequency flow field measurement system comprises a multi-cavity laser, an array CCD camera, a synchronous controller, a photoelectric signal acquisition and data processing device and a nanoparticle generator. According to the method, a sequence fine flow structure image and wall surface pressure distribution in the SWTBLI process within a certain incident shock wave intensity range can be measured, and blowing and suction flow control on a shock wave induction separation position and the size of a separation area can be realized, so that the size of the separation area is enhanced or weakened, the effect of shock waves on a boundary layer is changed, and the separation effect is improved. The characteristic time scale and the characteristic frequency of large-scale structures such as separation bubbles in an interference area can be analyzed through the image, so that the time evolution process of the SWTBLI flow structure, the experimental research on unsteady motion characteristics and the like can be favorably carried out; the blank that SWTBLI unsteady characteristic analysis is not synchronously carried out on the basis of image, pressure and blowing and sucking flow control at present in China is filled.

Description

technical field [0001] The present application relates to the technical field of aerodynamic experimental equipment, and in particular, relates to an experimental system and method for researching unsteady characteristics of SWTBLI. Background technique [0002] The Shock Wave / Turbulent Boundary Layer Interactions (SWTBLI) problem widely exists in the external and internal flows of various supersonic or hypersonic aircraft, and is a typical flow phenomenon that commonly exists during high-speed flight of aircraft. , mainly include plate-incident shock wave interference, compression corner, inner runner interference, swept back compression corner, column-skirt interference, etc. Shock wave and boundary layer interference is a complex flow phenomenon induced by the flow field on the incoming wall surface under the action of the reverse pressure gradient generated by the shock wave. In the process of shock wave and boundary layer interference, there are shock unsteady mechanism...

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Problems solved by technology

[0005] The embodiment of the present application provides an experimental system for the study of unsteady characteristics of SWTBLI, so as to solve the problem that the existing experimental technology for the study of unsteady characteristics of SWTBLI cannot realize the high-resolution time-correlated sequence fine flow structure and the measured flow field area Technical Problems of Simultaneous Measurement of Wall Pressure Distribution

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