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Description
An experimental and numerical study of high-speed gas-dynamic and thermal processes is carried out, which are realized during the simultaneous interaction of the plane shock wave (SW) and its co-flow with 1) shock tube test camera walls 2) the combined pulsed (submicrosecond) volume discharge in the test camera 3) the axisymmetric sphere-blunted cylinder model after volume discharge initiation. Computer Fluid Dynamics (CFD) simulations of the gas flow were performed and compared with panoramic data from high-speed shadow recording (150,000 fps) and infrared thermography imaging (up to 2,000 fps). Infrared radiation was recorded through the channel's side walls using a Telops FAST M200 camera.
CFD simulation of the compressible non-stationary gas flow was carried out using Navier-Stokes equations. The main goal of this simulation was to analyze the motion and evolution of the main flow discontinuities, as well as the effect of energy release and energy conversion to thermal fields. The effect of the discharge on the flow was simulated, the discharge energy converted to flow was determined. Various methods of the obtained numerical data visualization are used for adequate
matching CFD data with experimental data (shadowgraphy and thermography). Phenomena related to both plasma and gas-dynamic interactions in the shock tube test (discharge) chamber are investigated.
Through test camera quartz windows, transparent to the infrared radiation, images of non-stationary thermal fields, recorded by the infrared camera are obtained. They are: 1) thermal fields of the internal surfaces of the channel including side windows and model surfaces, heated for up to 200-300 microseconds by the cocurrent flow behind the SW due to thermal conductivity by the boundary layer 2) gas layer in front of the model (between the bow shock and model edge) heated during the stationary supersonic flow with bow shock 3) plasma radiation of a pulse volume discharge localized in front of the moving shock wave.
