@inproceedings{oai:jaxa.repo.nii.ac.jp:00004263,
 author = {小寺, 正敏 and 富岡, 定毅 and 植田, 修一 and 谷, 香一郎 and Kodera, Masatoshi and Tomioka, Sadatake and Ueda, Shuichi and Tani, Kouichiro},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication: Proceedings of 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012},
 month = {Mar},
 note = {第44回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2012 (2012年7月5日-6日. 富山国際会議場大手町フォーラム), 富山市, 富山県, 44th Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2012 (July 5-6, 2012. Toyama International Conference Center), Toyama Japan, In this study, numerical analysis was conducted for the scramjet mode operation of a JAXA H2 fueled rocket ramjet combined cycle engine called E3 under Mach 8 flight conditions. The objective of the study was to examine the effects of rocket chamber pressure, Pc and second fuel injection on the engine performance and related flow physics before the engine combustion tests. The calculation results revealed that the engine produced higher specific impulse as well as thrust with higher Pc; however, the thrust gain could hardly exceed the embedded rocket thrust. This is due to the fact that the rocket exhaust increased the friction drag on the combustor walls over the thrust due to combustion with the captured air and momentum addition of the rocket flow. On the other hand, the second fuel injection in the diverging combustor had almost no impact on the thrust augmentation even at low Pc conditions with a large amount of second fuel, resulting in "" reduction of the specific impulse contrary to expectations. This partially came from that at lower Pc the combustion efficiency was reduced because of the lower temperature and larger amount of H radical production as well as poorer fuel/air mixing., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0061958023, レポート番号: JAXA-SP-12-010},
 pages = {139--144},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {スクラムジェットモードにおけるロケット: ラムジェット複合エンジンの数値計算},
 volume = {JAXA-SP-12-010},
 year = {2013}
}