Numerical simulation of unsteady flow field on shock-induced combustion

K. Suzuki, A. Matsuo

研究成果: Paper査読

1 被引用数 (Scopus)

抄録

A three-dimensional numerical analysis that used two-step chemical reaction model was conducted on the unsteady combustion phenomenon around the supersonic flight body . Regular regime is a very steady mode, and the flow field where axisymmetric was strong. Influence of the grid resolution to the flow field was small. In Large-disturbance regime, the flow field was greatly changed by the changing the projectile diameter. The strength of the reaction shock was so strong that the reaction shocks interacted and distorted the leading bow shock wave strongly. Characteristic phenomena was observed in front of the projectile. Moreover, it has been understood that the flow field, greatly influences the grid resolution, exists.

本文言語English
出版ステータスPublished - 2009 1月 1
イベント7th Asia-Pacific Conference on Combustion, ASPACC 2009 - Taipei, Taiwan, Province of China
継続期間: 2009 5月 242009 5月 27

Conference

Conference7th Asia-Pacific Conference on Combustion, ASPACC 2009
国/地域Taiwan, Province of China
CityTaipei
Period09/5/2409/5/27

ASJC Scopus subject areas

  • 凝縮系物理学
  • エネルギー工学および電力技術
  • 燃料技術
  • 化学工学(全般)

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