@inproceedings{oai:jaxa.repo.nii.ac.jp:00003849,
 author = {谷, 洋海 and 寺島, 洋史 and 越, 光男 and 大門, 優 and Tani, Hiroumi and Terashima, Hiroshi and Koshi, Mituo and Daimon, Yu},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, Hydrazine (N2H4) nitrogen dioxide (NO2) co-flowing plane jets were simulated to explore the flame structures in hypergolic N2H4 nitrogen tetroxide (N2O4) bipropellant thrusters. The Navier-Stokes equations with a detailed chemical kinetics mechanism were solved in a manner of direct numerical simulation to reveal the interaction between fluid dynamics and the distinct chemical reaction, i.e. hydrogen abstraction by nitrogen dioxide (NO2) and the thermal decomposition of N2H4. The combustion flames uniquely comprised two types of flames, the diffusion flame and the decomposition flame. The diffusion flame came from the oxidization by NO2. The decomposition flame was caused by the heat transfer from the diffusion flame and a high rate of heat release from the thermal decomposition of N2H4. Owing to the decomposition flame, the decomposition products such as NH3, N2 and H2 became the major constituents of the downstream combustion gases., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023014, レポート番号: JAXA-SP-14-010},
 pages = {75--80},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {ヒドラジン/二酸化窒素同軸噴流の特異な二重火炎構造},
 volume = {JAXA-SP-14-010},
 year = {2015}
}