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2)
2012 年 11 巻 p. 85-88
詳細
2012 年 11 巻 p. 85-88
In the Part-2, it is continuing to examine the presenting combustion model to LOX/methane combustion at supercritical pressure. Then the model is expanded to apply for design and evaluation method of actual rocket combustion chamber at supercritical combustion pressure.
