Head-on interaction of shock waves and vortex rings with solid and perforated walls

D. Kounadis; R. An; H. Zare-Behtash; K. Kontis; J. A. Edwards

Head-on interaction of shock waves and vortex rings with solid and perforated walls

D. Kounadis, R. An, H. Zare-Behtash, K. Kontis, J. A. Edwards

Research output: Chapter in Book/Conference proceeding › Conference contribution › peer-review

Abstract

An experimental study has been conducted to examine the interaction of a shock wave and a vortex ring with a flat plate and a perforated plate. The experiments were carried out using a 30mm internal diameter shock-tube. The driver and driven gas was air. High-speed Schlieren photography was employed to study the development of the flow-field and the resulting interactions with the plates. Wall pressure measurements were also carried out to study the flow quantitatively at the exit of the shock-tube. Three different driver pressures of 4, 8 and 12bar were examined under critical driver length conditions; the shock wave Mach number was 1.33, 1.52 and 1.67, respectively.

Original language	English
Title of host publication	Collection of Technical Papers - 36th AIAA Fluid Dynamics Conference\|Coll. Tech. Pap. AIAA Fluid Dynam. Conf.
Pages	115-138
Number of pages	23
Volume	1
Publication status	Published - 2006
Event	36th AIAA Fluid Dynamics Confernce - San Francisco, CA Duration: 1 Jul 2006 → …

Conference

Conference	36th AIAA Fluid Dynamics Confernce
City	San Francisco, CA
Period	1/07/06 → …

Keywords

AIAA 2006-2875

Cite this

@inproceedings{dc39f9015d85425c9a783796be1bdf13,

title = "Head-on interaction of shock waves and vortex rings with solid and perforated walls",

abstract = "An experimental study has been conducted to examine the interaction of a shock wave and a vortex ring with a flat plate and a perforated plate. The experiments were carried out using a 30mm internal diameter shock-tube. The driver and driven gas was air. High-speed Schlieren photography was employed to study the development of the flow-field and the resulting interactions with the plates. Wall pressure measurements were also carried out to study the flow quantitatively at the exit of the shock-tube. Three different driver pressures of 4, 8 and 12bar were examined under critical driver length conditions; the shock wave Mach number was 1.33, 1.52 and 1.67, respectively.",

keywords = "AIAA 2006-2875",

author = "D. Kounadis and R. An and H. Zare-Behtash and K. Kontis and Edwards, \{J. A.\}",

year = "2006",

language = "English",

isbn = "1563478102",

volume = "1",

pages = "115--138",

booktitle = "Collection of Technical Papers - 36th AIAA Fluid Dynamics Conference|Coll. Tech. Pap. AIAA Fluid Dynam. Conf.",

note = "36th AIAA Fluid Dynamics Confernce ; Conference date: 01-07-2006",

}

TY - GEN

T1 - Head-on interaction of shock waves and vortex rings with solid and perforated walls

AU - Kounadis, D.

AU - An, R.

AU - Zare-Behtash, H.

AU - Kontis, K.

AU - Edwards, J. A.

PY - 2006

Y1 - 2006

N2 - An experimental study has been conducted to examine the interaction of a shock wave and a vortex ring with a flat plate and a perforated plate. The experiments were carried out using a 30mm internal diameter shock-tube. The driver and driven gas was air. High-speed Schlieren photography was employed to study the development of the flow-field and the resulting interactions with the plates. Wall pressure measurements were also carried out to study the flow quantitatively at the exit of the shock-tube. Three different driver pressures of 4, 8 and 12bar were examined under critical driver length conditions; the shock wave Mach number was 1.33, 1.52 and 1.67, respectively.

AB - An experimental study has been conducted to examine the interaction of a shock wave and a vortex ring with a flat plate and a perforated plate. The experiments were carried out using a 30mm internal diameter shock-tube. The driver and driven gas was air. High-speed Schlieren photography was employed to study the development of the flow-field and the resulting interactions with the plates. Wall pressure measurements were also carried out to study the flow quantitatively at the exit of the shock-tube. Three different driver pressures of 4, 8 and 12bar were examined under critical driver length conditions; the shock wave Mach number was 1.33, 1.52 and 1.67, respectively.

KW - AIAA 2006-2875

UR - https://www.scopus.com/pages/publications/33845249153

M3 - Conference contribution

SN - 1563478102

SN - 9781563478109

VL - 1

SP - 115

EP - 138

BT - Collection of Technical Papers - 36th AIAA Fluid Dynamics Conference|Coll. Tech. Pap. AIAA Fluid Dynam. Conf.

T2 - 36th AIAA Fluid Dynamics Confernce

Y2 - 1 July 2006

ER -

Head-on interaction of shock waves and vortex rings with solid and perforated walls

Abstract

Conference

Keywords

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