Comparison of Turbulence models in Openfoam for 3D Simulation of Solid Propellant Rocket Engine

Authors

  • Pavel Konečný University of Defence, Brno, Czech Republic
  • Radek Ševčík Masaryk University, Brno, Czech Republic

DOI:

https://doi.org/10.3849/aimt.01131

Keywords:

turbulent flow, turbulent model, solid propellant rocket engine, OpenFOAM

Abstract

This paper deals with comparison of various mathematical models for simulating turbulent flow in a solid propellant rocket engine. For comparison, the most used models were selected and simulations of flow in a rocket engine type S5 were made for which experimental data are available and which allows comparison of the simulation results with reality. The best results are achieved with LES Smagorinsky model, while type RANS models are not good for this type of task.

Author Biographies

  • Pavel Konečný, University of Defence, Brno, Czech Republic

    Department of weapons and ammunition, professor

  • Radek Ševčík, Masaryk University, Brno, Czech Republic

    Institute of experimental biology, IT specialist

References

SEVCIK, R. Simulation of processes in rocket engine (in Czech) [PhD thesis]. Brno: University of Defence, 2016.

HOLZINGER, G. OpenFOAM – a Little User-Manual. Linz: Johannes Kepler University, 2015, 251 p.

URUBA, V. Turbulence(in Czech) [Textbook]. Prague: CTU, 2009.

VLCEK, P. Turbulent Flow Modelling. InProceedings of Conference on Pro-cessing Technology 2013. Prague: CTU, 2013.

MYNARIK, P. Influence of Combustion Products of Solid Propellant on the Course of Processes in the Solid Propellant Rocket Motor (in Czech) [PhD the-sis]. Brno: University of Defence, 2007.

LUDVIK, F. and KONECNY, P.Internal Ballistics of Solid Propellant Rocket Motors (in Czech) [Textboook]. Brno: Military Academy in Brno, 1999, 208 p.

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Published

25-12-2016

Issue

Section

Research Paper

Categories

How to Cite

Konečný, P., & Ševčík, R. (2016). Comparison of Turbulence models in Openfoam for 3D Simulation of Solid Propellant Rocket Engine. Advances in Military Technology, 11(2), 239-251. https://doi.org/10.3849/aimt.01131

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