@techreport{oai:jaxa.repo.nii.ac.jp:00041178,
 author = {田丸, 卓 and 下平, 一雄 and 斎藤, 隆 and 山田, 秀志 and Tamaru, Takashi and Shimodaira, Kazuo and Saito, Takashi and Yamada, Hideshi},
 month = {Mar},
 note = {宇宙往還機用エアブリージングエンジンのラム燃焼器に関する基礎的試験を行った結果である。想定される実機の約1/10の直径155mmの筒により、マッハ3までの作動条件に対する水素燃料燃焼特性を実験的に調べた。全圧・静圧の計測により圧力損失、ガス温度を求め、半径方向局所ガス採取によって、燃料/空気の混合と燃焼効率の関係を求めた。これにより保炎器の配置などによる流れと燃料の混合が燃焼効率に重大な影響を与えることを明らかにした。, To obtain design data of a subsonic ram-combustor for a hypersonic plane, hydrogen combustion tests were made using an approximately one tenth scale model. The model was composed of a constant area combustion duct 150 mm in diameter, flame holders and a centerbody which simulates the turbo-fan engine part to be used as a booster for the take-off mode. The tested conditions of supplied air velocity, air temperature and mixture strength were equivalent to those of the combustor inlet at flight speeds ranging from take-off to Mach 3. Gas velocity and temperature distributions along the axis, and the values of total pressure loss were obtained by measurements of total and static pressures. The combustion efficiency was derived from analysis of the sampled gas at the exit. It was found that the fuel distribution in the combustor exerts a significant effect on combustion efficiency, particularly near the stoichiometric mixture condition., 資料番号: AA0004208000, レポート番号: NAL TR-1193},
 title = {極超音速機用水素燃料ターボラム燃焼器模型の試験結果},
 year = {1993}
}