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.
|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 24 → 2009 5月 27
|Conference||7th Asia-Pacific Conference on Combustion, ASPACC 2009|
|国/地域||Taiwan, Province of China|
|Period||09/5/24 → 09/5/27|
ASJC Scopus subject areas