Shock Tube Boundary Layer Measurements with 4 Visualization Digital Methodsстатья

Дата последнего поиска статьи во внешних источниках: 24 января 2020 г.

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[1] Shock tube boundary layer measurements with 4 visualization digital methods / I. A. Znamenskaya, F. N. Glazirin, T. A. Kuli-Zade, D. I. Tatarenkova // The 15th international conference on fluid control, measurements, and visualization (FLUCOME). — Italy: Italy, 2019. — P. ID322–1–ID322–2. High-speed gas flow in shock tube with special discharge test section has been studied with four visualization methods: Particle Image Velocimetry (PIV); high speed shadowgraphy recording with digital CCD cameras, particle tracing and; pulse discharge visualization method. The flow evolution was recorded for 12 ms after shock wave with Mach number range from M = 1,3 to M = 4,0 had passed by windows. Boundary layer transition on the walls was investigated with optical methods. It was shown that with the Mach number of the incident shock wave 3, a boundary layer is visualized 100 μs after the passage of the shock wave; a subsonic flow with a speed of 200m lasts up to 10 ms.

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