航空宇宙技術
Online ISSN : 1884-0477
液酸・液水ロケットエンジン超臨界圧燃焼マクロモデル(その1)
八柳 信之
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ジャーナル フリー

2012 年 11 巻 p. 79-84

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This paper describes a study of combustion process of LOX/hydrogen rocket engine at supercritical pressure by macroscopic model. The model consists of rate controlling one by mixing process of supercritical temperature oxygen with hydrogen. Here, local mixing efficiency of the propellants is evaluated by Rupe's mixing index. And if we assumed that the local combustion rate was related to the Rupe's index as the exponential function, then the pressure distribution of combustion along chamber length calculated by the presented model could duplicate the pressure distribution observed by the experiments.

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© 2012 The Japan Society for Aeronautical and Space Sciences
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