Head-on collision of shock wave induced vortices with solid and perforated walls

Abstract

An experimental study has been conducted to examine the interaction of shock wave induced vortices with a flat plate and a perforated plate. The experiments were carried out using a 30 mm internal diameter shock-tube at Mach numbers 1.31, 1.49, and 1.61 under critical driver conditions. Air was used both in the driver and driven sections. High-speed schlieren photography was employed to study the flow development and the resulting interactions with the plates. Wall pressure measurements on both plates were also carried out in order to study the flow interactions quantitatively. The experimental results indicated that a region of strong flow development is generated near the wall surface, due to the flow interactions of reflected waves and oncoming induced vortices. This flow behavior causes the generation of multiple pressure fluctuations on the wall. In the case of the perforated plate, a weaker initial reflected wave is produced, which is followed by compression waves, due to the internal reflections within the plate. The transmitted wave is reduced in strength, compared to the initial incident shock wave.

Effectiveness of jet location on mixing characteristics inside a cavity in supersonic flow

“…1, where γ is the specific heat ratio, ρ is the density, M is the Mach number and subscripts 0 and jet refer to freestream and jet conditions. Schlieren photography [40][41][42][43][44] was employed to visualize the flow field around the cavity in a standard Z-type optical arrangement. A pair of 203.3 mm diameter parabolic mirrors with 1016 mm focal length and a 150W Hamamatsu Xenon continuous light source were used.…”

Effect of primary jet geometry on ejector performance: A cold-flow investigation

“…This produces a pulsed upstream condition where the duration and magnitude of the pulse can be controlled up to the nozzles' inlet. [11][12][13] The length of the circular driven section (baseline) was 1310.5mm, with each nozzle 300mm in length.…”

Global visualization and quantification of compressible vortex loops

“…The bursting of the diaphragm was initiated manually with a plunger. The shock tube setup was identical to that used by Kontis et al (2008).…”

“…In order to better compare the vortex loop behavior at various Mach numbers, it is desirable to eliminate these distortions. A means of doing so is by changing the length of the driver section so that the incident shock and the initial reflected rarefaction wave arrive at the shock tube exit at approximately the same time (Kontis et al, 2008, Arakeri et al, 2004, Brouillette and Hebert, 1997.…”