@article{oai:jaxa.repo.nii.ac.jp:00021747,
 author = {角銅, 洋実 and 榊, 和樹 and 中谷, 辰爾 and 津江, 光洋 and 金井, 竜一郎 and 稲川, 貴大 and 平岩, 徹夫 and Kakudo, Hiromitsu and Sakaki, Kazuki and Nakaya, Shinji and Tsue, Mitsuhiro and Kanai, Ryuichiro and Inagawa, Takahiro and Hiraiwa, Tetsuo},
 issue = {1},
 journal = {日本航空宇宙学会論文集, Journal of the Japan Society for Aeronautical and Space Sciences},
 month = {Feb},
 note = {The pintle injector is a promising candidate for injection systems of future rocket engines because of the throttling capability, the combustion stability, and the low manufacturing cost. Few studies focusing on fundamental aspects of a pintle injector have been conducted, and most of the design parameters of a pintle injector is determined mainly based on the empirical knowledge. Among the design parameters, total momentum ratio (TMR) is one of the most important parameters since spray structure is dominated by TMR. Therefore, combustion experiments using an ethanol/liquid oxygen rocket engine combustor with a planar pintle-type injector which is designed for optical measurements for a pintle injector are conducted at combustion pressure (P(sub c)) = 0.37-0.42MPa, mixture ratio (O/F) = 1.31-1.49, TMR = 0.32-3.65 to investigate the effects of propellant momentum ratio on the combustion behavior. The spray structure under hot fire conditions is observed using high-speed imaging techniques with a backlit configuration. In the oxidizer-centered configuration, the characteristic exhaust velocity efficiency (η(sub C*)) decreases with the increase of the TMR. The atomized propellant impinge on the combustor wall before the vaporization and reaction at higher TMR. In the fuel-centered configuration, though the propellant spray is more inclined to the direction of the upper combustor wall at higher TMR, the η(sub C*) does not change with the TMR. In both oxidizer-centered and fuel-centered, higher η(sub C*) is provided in the condition of higher injection pressure drop., 形態: 図版あり, Physical characteristics: Original contains illustrations, 資料番号: DS1640317001},
 pages = {1(1)--9(9)},
 title = {エタノール/液体酸素ロケットエンジン燃焼室における平面ピントル型噴射器の推進剤噴射運動量比が燃焼挙動に及ぼす影響},
 volume = {65},
 year = {2017}
}