Numerical Analysis of Sloshing and Wave Breaking in a Small Vessel by CIP-LSM

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  • HIMENO Takehiro
    Department of Aeronautics and Astronautics, University of Tokyo
  • WATANABE Toshinori
    Department of Aeronautics and Astronautics, University of Tokyo
  • NONAKA Satoshi
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • NARUO Yoshihiro
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency
  • INATANI Yoshifumi
    Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency

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Description

For the prediction of sloshing in the propellant tank of a rocket vehicle, the preliminary investigation was conducted. The flow field in the propellant tank during the ballistic flight of the vehicle was experimentally reproduced with the sub-scale model. The lateral acceleration as large as about 0.8G was provided with a mechanical exciter and the deformation of the liquid surface in the small vessel was visualized with a high-speed camera. The sloshing phenomena were also simulated with the CFD code, called CIP-LSM. The important features of surface deformation and wave breaking were successfully reproduced in the computation.

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