Abstract
Shock wave motion is important in many areas of engineering like blast wave modeling, aeronautical design, medical applications, etc. Previous works mostly emphasized on sharp geometry responsible for flow separation immediately. In present study, shock diffraction over round corner is investigated solely and the intricate flow features are summarized. Numerical simulations are performed using Finite Volume Method. The rounded geometry requires laminar viscosity model due to continuous changes of the orientation. The unsteady flow field is designed to have an understanding appropriate to the test cases in real practice. Shear layer, vortex generation, secondary and recompression shock waves, etc. are clearly investigated. Induced flow velocity reaches supersonic level after being passed by the convergent-divergent passage and thereafter shocked to gets reduced in magnitude. Internal terminating shock compresses the flow to a relatively higher pressure to curve the shear layer in opposite direction. Beginning of separation and change in curvature of shear layer indicates more vortex strength than the primary vortex core.
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Acknowledgements
This paper is a revised and expanded version of an article entitled ‘Computational Study of Shock Diffraction over Rounded Corners’ presented in ‘2nd International Conference on Energy Resources and Technologies for Sustainable Development’ held at IIEST Shibpur, Howrah, India during 27-28 April 2023.
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All authors contributed to the study and design. Material preparation, data collection and analysis were performed by all authors. The first draft of the manuscript was written by Debiprasad Banerjee and all authors commented on previous versions. All authors read and approved the final manuscript.
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Banerjee, D., Halder, P. Numerical Analysis of Shock Diffraction over Rounded Corner. J. Inst. Eng. India Ser. C (2024). https://doi.org/10.1007/s40032-024-01049-9
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DOI: https://doi.org/10.1007/s40032-024-01049-9