Shock wave-induced vortex loops emanating from nozzles with singular corners
Shock wave-induced vortex loops emanating from nozzles with singular corners
The focus of the current study is to examine experimentally the diffracted shock wave pattern and the consequent vortex loop formation, propagation, and decay from nozzles having singular corners. Non-intrusive qualitative and quantitative techniques: schlieren, shadowgraphy, and particle image velocimetry (PIV) are employed to analyze the induced flow-fields. Eye-shaped nozzles were used with the corner joints representing singularities. The length of the minor axes are a = 6 and 15 mm, with the major axis b = 30 mm for both cases. The experiments are performed for flow Reynolds numbers in the range 0.8 × 105 and 4.6 × 105. Air is used in both driver and driven sections of the shock tube.
1005–1019
Zare-Behtash, H.
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, K.
e40ecdbc-e5e9-4522-abf9-e3c3f3c2d7fa
Gongora-Orozco, N.
ad84ae2a-c214-4d5e-8f56-72caea445273
Takayama, K.
5ce4b71e-6076-48a0-b142-b89ce2a23621
6 March 2010
Zare-Behtash, H.
74be9b97-cb09-49c6-9f75-7ec58c0dd16c
Kontis, K.
e40ecdbc-e5e9-4522-abf9-e3c3f3c2d7fa
Gongora-Orozco, N.
ad84ae2a-c214-4d5e-8f56-72caea445273
Takayama, K.
5ce4b71e-6076-48a0-b142-b89ce2a23621
Zare-Behtash, H., Kontis, K., Gongora-Orozco, N. and Takayama, K.
(2010)
Shock wave-induced vortex loops emanating from nozzles with singular corners.
Experiments in Fluids, 49, .
(doi:10.1007/s00348-010-0839-7).
Abstract
The focus of the current study is to examine experimentally the diffracted shock wave pattern and the consequent vortex loop formation, propagation, and decay from nozzles having singular corners. Non-intrusive qualitative and quantitative techniques: schlieren, shadowgraphy, and particle image velocimetry (PIV) are employed to analyze the induced flow-fields. Eye-shaped nozzles were used with the corner joints representing singularities. The length of the minor axes are a = 6 and 15 mm, with the major axis b = 30 mm for both cases. The experiments are performed for flow Reynolds numbers in the range 0.8 × 105 and 4.6 × 105. Air is used in both driver and driven sections of the shock tube.
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Accepted/In Press date: 29 January 2010
Published date: 6 March 2010
Identifiers
Local EPrints ID: 491730
URI: http://eprints.soton.ac.uk/id/eprint/491730
ISSN: 0723-4864
PURE UUID: f944d408-1b49-405a-b8ac-c6a877a54187
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Date deposited: 03 Jul 2024 16:56
Last modified: 11 Jul 2024 02:18
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Contributors
Author:
H. Zare-Behtash
Author:
K. Kontis
Author:
N. Gongora-Orozco
Author:
K. Takayama
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