@article{oai:jaxa.repo.nii.ac.jp:00022444,
 author = {小室, 智幸 and 富岡, 定毅 and Takagi, Shohei and 高橋, 政浩 and 植田, 修一 and 伊藤, 勝宏 and Komuro, Tomoyuki and Tomioka, Sadatake and Takagi, Shohei and Takahashi, Masahiro and Ueda, Shuichi and Itoh, Katsuhiro},
 issue = {ists29},
 journal = {Transactions of the Japan Society for Aeronautical and Space Sciences, Aerospace Technology Japan},
 month = {Jul},
 note = {Combination of a scramjet (supersonic combustion ramjet) flow-pass with embedded rocket engines (the combinedsystem termed as Rocket Based Combined Cycle engine) are expected to be the most effective propulsion system forBooster stage of space launch vehicles. At hypersonic regime, it will be operated at rather high rocket engine output forfinal acceleration with some Isp gains due to air-breathing effects. In this regime, attaining thrust at this high-speedregime becomes very difficult, so that parallel injection of the fuel for scramjet combustion is favorable as the momentumof the injection can contribute to the thrust production. Thus, embedded rocket chamber was supposed to the operated asfuel rich gas generator at very high output. This configuration was tested at simulated flight Mach number of 11 at HighEnthalpy Shock Tunnel (HIEST) with detonation tube as the source of the simulated rocket exhaust. However,combustion of the residual fuel in the rocket exhaust with airflow could not be attained in the past study, so thatmodification was carried out. Combustion was attained within the combustor, however, insufficient mixing was found toresponsible for the rather low combustion efficiency, finding being from complementary mixing test at a blow-down typetunnel., 資料番号: PA1410085000},
 pages = {Pa_71--Pa_77},
 title = {Combustion Phenomena within a RBCC Engine under Scramjet-mode Operation},
 volume = {12},
 year = {2014}
}