@techreport{oai:jaxa.repo.nii.ac.jp:00002738,
 author = {清水, 和弥 and 伊藤, 隆 and 根岸, 秀世 and 清水, 太郎 and 山西, 伸宏 and Shimizu, Kazuya and Ito, Takashi and Negishi, Hideyo and Shimizu, Taro and Yamanishi, Nobuhiro},
 month = {Oct},
 note = {Numerical simulation has been carried out to support the development of the H-2A launch vehicle and the LNG propulsion system. Numerical results reveal the mixed flow field with hot hydrogen and cold hydrogen in a liquid rocket engine of the H-2A. The local erosion results from the change of the heat flux to the concavity and convexity of the fin in the solid rocket booster (SRB-A). In the LNG propulsion system, it is indicated from the numerical evaluation that the increase of the pressure in the combustion chamber and the decrease in the chemical non-equilibrium loss are required in order to improve the engine performance. The effect of the film cooling inside the igniter is shown and the flame temperature was estimated. The consumption of helium gas at the flight is evaluated by the numerical analysis., 資料番号: AA0047944007, レポート番号: JAXA-RM-04-009},
 title = {H-2AロケットおよびLNG推進系の開発を支援するCFD解析},
 year = {2004}
}