@inproceedings{oai:jaxa.repo.nii.ac.jp:00016614,
 author = {富岡, 定毅 and 泉川, 宗男 and 増本, 量 and 山岬, 裕之 and 松尾, 亜紀子 and Tomioka, Sadatake and Izumikawa, Muneo and Masumoto, Ryo and Yamasaki, Hiroyuki and Matsuo, Akiko},
 book = {宇宙輸送シンポジウム: 講演集録, Proceedings of Space Transportation Symposium},
 month = {Jan},
 note = {平成21年度宇宙輸送シンポジウム(2010年1月14日-15日, 宇宙航空研究開発機構宇宙科学研究本部), Space Transportation Symposium (January 14-15, 2010. Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency(JAXA)),  Sagamihara, Kanagawa Japan, Supersonic injections through diamond-shaped injectors were applied to a supersonic combustor with a diverging section, with a Mach 2.4 incoming vitiated airflow at a total temperature of 2000 K, and combustion characteristics were experimentally investigated and compared to those with sonic injection through circular injectors. Without any flame-holding devices installed, scramjet-mode combustion was attained in wide range of fuel flow rate, in which the supersonic injections resulted in a higher pressure-rise in far-field than the sonic injections. Regardless of the injection scheme (i.e, orifice shape, orifice number, and injection conditions), transition to dual-mode combustion enhanced the thrust production, and the supersonic injection through the diamond-shaped orifice had lesser ability to cause the transition than the sonic injection through the circular orifice. The ability was enhanced by installation of a recess and introduction of recess fueling, and resulting combustor performance was slightly better than that with the sonic injection., 形態: CD-ROM1枚, Note: One CD-ROM, 資料番号: AA0064741044},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA)},
 title = {菱形孔超音速噴射器を用いたラム・スクラムモード燃焼},
 volume = {平成21年度},
 year = {2010}
}