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Shock Tube Boundary Layer Measurements with 4 Visualization Digital Methodsстатья
- Авторы: Znamenskaya I.A., Glazirin F.N., Kuli-Zade T.A., Tatarenkova D.I.
- Сборник: The 15th international conference on fluid control, measurements, and visualization (FLUCOME)
- Год издания: 2019
- Издательство: University of Naples Federico II
- Местоположение издательства: Italy
- Первая страница: ID322-1
- Последняя страница: ID322-2
- Аннотация: 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.
- Добавил в систему: Долбня Дарья Илларионовна