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Shock wave-induced vortex loops emanating from nozzles with singular corners

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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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Acknowledgments

The authors are indebted to the technical staff at The University of Manchester for their assistance and for the help and advice of Dr. Martin Hyde (TSI) for the installation and setup of the PIV system. The support of the EPSRC Engineering Instrument Pool especially Mr. Adrian Walker, for the loan of the PIV system, is greatly acknowledged.

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Authors and Affiliations

  1. Spirit Aerosystems (UK), Prestwick International Airport, Ayrshire, KA9 2RW, UK

    H. Zare-Behtash

  2. School of MACE, The University of Manchester, M60 1QD, Manchester, UK

    K. Kontis & N. Gongora-Orozco

  3. Tohoku University, Shock Wave Research Centre, Sendai, 980-8577, Japan

    K. Takayama

Authors
  1. H. Zare-Behtash
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  2. K. Kontis
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  3. N. Gongora-Orozco
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  4. K. Takayama
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Correspondence to K. Kontis.

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Zare-Behtash, H., Kontis, K., Gongora-Orozco, N. et al. Shock wave-induced vortex loops emanating from nozzles with singular corners. Exp Fluids 49, 1005–1019 (2010). https://doi.org/10.1007/s00348-010-0839-7

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  • DOI: https://doi.org/10.1007/s00348-010-0839-7

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