@inproceedings{oai:jaxa.repo.nii.ac.jp:00047331,
 author = {小寺, 正敏 and 富岡, 定毅 and 宗像, 利彦 and 三谷, 徹 and KODERA, Masatoshi and TOMIOKA, Sadatake and MUNAKATA, Tohsihiko and MITANI, Toru},
 book = {宇宙航空研究開発機構特別資料: 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2020オンライン論文集, JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online},
 month = {Feb},
 note = {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2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), In this study, three-dimensional CFD analysis was carried out for a hydrogen fueled scramjet engine tested at the Ramjet Engine Test Facility (RJTF) under Mach 6 flight conditions. As a result, for a fuel equivalence ratio of 0.3, various combustion modes were observed depending on the combustor wall temperature, operation of igniter, presence of water vapor in air conditions as well as initial solutions. Those combustion modes were classified into 4 groups: Partially-anchored, Fully-anchored, Partially-blow-off and Blow-off modes, from the point of view of flame anchor point, and were investigated in detail. In addition, it was demonstrated that several combustion phenomena occurred in the RJTF tests corresponded to one of them., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030013010, レポート番号: JAXA-SP-20-008},
 pages = {69--78},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {CFD模擬によるスクラムジェットエンジン内の諸燃焼形態について},
 volume = {JAXA-SP-20-008},
 year = {2021}
}