Application of immersed boundary method with wall injection for solid rocket motor internal flow

Takuya Hirose, Shinichiro Ogawa, Daisuke Sasaki, Yuma Fukushima, Shigeru Obayashi

研究成果: Conference contribution

抄録

The vortex shedding in combustion chamber of solid rocket motor may lead the pressure oscillations, which deteriorates the rocket motor performance and could even damage the payload. Cartesian mesh CFD solver is expected to accurately predict such vortex flows using higher-order scheme and to treat complicated configurations easily. Therefore, blockstructured Cartesian mesh solver, Building-Cube Method (BCM), is applied to Taylor flow analysis, which is the simplified combustion chamber model of solid rocket. Immersed boundary method is extended to treat the wall injection from the grain surface. The approach is also applied to real grain configuration, and the usefulness for the complicated geometry is validated.

本文言語English
ホスト出版物のタイトルAIAA Modeling and Simulation Technologies Conference, 2017
出版社American Institute of Aeronautics and Astronautics Inc, AIAA
ISBN(印刷版)9781624104510
出版ステータスPublished - 2017 1 1
イベントAIAA Modeling and Simulation Technologies Conference, 2017 - Grapevine, United States
継続期間: 2017 1 92017 1 13

出版物シリーズ

名前AIAA Modeling and Simulation Technologies Conference, 2017

Other

OtherAIAA Modeling and Simulation Technologies Conference, 2017
国/地域United States
CityGrapevine
Period17/1/917/1/13

ASJC Scopus subject areas

  • 航空宇宙工学
  • モデリングとシミュレーション

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