School of Engineering, University of Tokyo
University of Ulster
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)(ISAS)
出版者
宇宙航空研究開発機構宇宙科学研究本部
出版者（英）
Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)
Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)), Sagamihara, Kanagawa Japan
抄録（英）
The purpose of this study is to develop a calculation code to simulate flowfields in combustion chambers of hybrid rockets. As the first step, quasi-one-dimensional steady flowfield is simulated with a fast chemistry model. Mass addition is estimated by solving heat balance at the solid fuel surface with Karabeyoglu's and Hanzawa's heat feedback models.
内容記述
形態: カラー図版あり
形態: CD-ROM1枚
内容記述（英）
Physical characteristics: Original contains color illustrations
Note: One CD-ROM
燃料後退速度の依存特性を考慮したハイブリッドロケット定常燃焼解析
