Abstract
This paper presents numerical simulations of three-dimensional flow separation in a supersonic over-expanded nozzle with a Thrust-Optimized Contour (TOC). Computations are conducted for various nozzle pressure ratio (NPR) in order to investigate the effect of the pressure gradient on the shock structure and the associated flow unsteadiness. By analyzing the pressure signals downstream of the separation, it is found that the high-energy large-amplitude movement of the recirculation flow behind the Mach disk leads to shock unsteadiness and strong pressure fluctuations at the wall. The study highlights for the first time the importance of the flow unsteadiness downstream of the separation and the role played by the own dynamics of the recirculating zone and the associated vortex core on the overall nozzle flow instabilities.
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Acknowledgements
The first author is supported financially by the DGA (Direction Générale de l’Armement) from the French Ministry of Defense in collaboration with the DSTL, UK. The authors wish to thank the European PRACE project which allocated computer core-hours as part of the 9th PRACE project call. The simulations have been achieved using the TGCC Curie Fat Node cluster of CEA in France.
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Piquet, A., Georges-Picot, A., Hadjadj, A. (2017). Unsteadiness of Supersonic Flows in Over-Expanded Nozzles. In: Ben-Dor, G., Sadot, O., Igra, O. (eds) 30th International Symposium on Shock Waves 1. Springer, Cham. https://doi.org/10.1007/978-3-319-46213-4_18
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DOI: https://doi.org/10.1007/978-3-319-46213-4_18
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