Numerical investigation of the gas-particle flow in the shock tube using discrete particle and continuum model

Akihito Kimura, Akiko Matsuo

Research output: Chapter in Book/Report/Conference proceedingConference contribution

2 Citations (Scopus)

Abstract

The numerical investigation of the gas-particle flow in the shock tube is conducted using the continuum model (Two-Fluid model) and the discrete particle model (CFD-DEM). From calculated results of both methods, particles are concentrated at downstream edge of particle bed and dispersed at upstream edge of particle bed with the passage of time. The incident shock wave is divided into the reflected shock and the transmitted shock because of interactions with particles. These flow field can be observed in the experiment conducted by Rogue et al., and Two-Fluid model and CFD-DEM can qualitatively reproduce the interaction phenomena between shock wave and particles. In the experiment, the pressure oscillations behind the reflected and the transmitted shock wave are observed as well as CFD-DEM, but no oscillation is seen in Two-Fluid model. Therefore, Two-Fluid model can qualitatively reproduce the interaction phenomena of shock wave and particles qualitatively, although the behavior of individual particle is neglected in the model.

Original languageEnglish
Title of host publication2018 Fluid Dynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624105531
DOIs
Publication statusPublished - 2018 Jan 1
Event48th AIAA Fluid Dynamics Conference, 2018 - Atlanta, United States
Duration: 2018 Jun 252018 Jun 29

Other

Other48th AIAA Fluid Dynamics Conference, 2018
CountryUnited States
CityAtlanta
Period18/6/2518/6/29

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ASJC Scopus subject areas

  • Aerospace Engineering
  • Engineering (miscellaneous)

Cite this

Kimura, A., & Matsuo, A. (2018). Numerical investigation of the gas-particle flow in the shock tube using discrete particle and continuum model. In 2018 Fluid Dynamics Conference [AIAA 2018-3550] American Institute of Aeronautics and Astronautics Inc, AIAA. https://doi.org/10.2514/6.2018-3550