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Hybrid RANS/LES Simulation of Shock-Induced Separated Flow in Truncated Ideal Contour Nozzle

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31st International Symposium on Shock Waves 2 (ISSW 2017)

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Abstract

The present study is motivated by the flow analysis of supersonic nozzles used in the rocket launcher, more specifically about the generation of side loads. The work aims at identifying and at modeling the dominant elements of the organized structure of the flow in overexpanded rocket nozzles.

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Acknowledgements

The work presented is part of the nozzle research project ATAC led by the French Space Center (CNES). This work was performed using HPC resources from GENCI [TGCC] (Grant 2017 [A0012A10017]).

Author information

Authors and Affiliations

  1. ENSMA, Institut Pprime, UPR 3346, CNRS, Chasseneuil-du-Poitou, France

    Eric Goncalves, B. Guillaume Lehnasch & C. Julien Herpe

  2. Centre National d’Études Spatiales (CNES) – Direction des Lanceurs, Paris, France

    B. Guillaume Lehnasch & C. Julien Herpe

Authors
  1. Eric Goncalves
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  2. B. Guillaume Lehnasch
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  3. C. Julien Herpe
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Editor information

Editors and Affiliations

  1. Department of Aerospace Engineering, Nagoya University, Nagoya, Japan

    Akihiro Sasoh

  2. Department of Energy and Environmental Engineering, Kyushu University, Kasuga, Fukuoka, Japan

    Toshiyuki Aoki

  3. Institute of Innovative Research, Tokyo Institute of Technology, Tokyo, Japan

    Masahide Katayama

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Goncalves, E., Lehnasch, B.G., Herpe, C.J. (2019). Hybrid RANS/LES Simulation of Shock-Induced Separated Flow in Truncated Ideal Contour Nozzle. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 2. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91017-8_65

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  • DOI: https://doi.org/10.1007/978-3-319-91017-8_65

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  • Publisher Name: Springer, Cham

  • Print ISBN: 978-3-319-91016-1

  • Online ISBN: 978-3-319-91017-8

  • eBook Packages: EngineeringEngineering (R0)

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