Numerical simulation of unsteady flow field on shock-induced combustion

K. Suzuki, A. Matsuo

研究成果: Paper

1 引用 (Scopus)

抜粋

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.

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

Conference

Conference7th Asia-Pacific Conference on Combustion, ASPACC 2009
Taiwan, Province of China
Taipei
期間09/5/2409/5/27

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Energy Engineering and Power Technology
  • Fuel Technology
  • Chemical Engineering(all)

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  • これを引用

    Suzuki, K., & Matsuo, A. (2009). Numerical simulation of unsteady flow field on shock-induced combustion. 論文発表場所 7th Asia-Pacific Conference on Combustion, ASPACC 2009, Taipei, Taiwan, Province of China.