@inproceedings{oai:jaxa.repo.nii.ac.jp:00003502,
 author = {谷, 洋海 and 大門, 優 and 梅村, 悠 and 根岸, 秀世 and Tani, Hiroumi and Daimon, Yu and Umemura, Yutaka and Negishi, Hideyo},
 book = {宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34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 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川, 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan, A feasibility study of the interface tracking simulations of liquid oxygen (LOX) and gaseous hydrogen(GH2) coaxial combustion at a subcritical pressure was conducted. To simulate the breakup and atomization of LOX core, CIP-LSM (Constrained Interpolation Profile based Level Set and MARS) that combined CIP-CUP (CIP-Combined Unified Procedure) method with the hybrid Level-set and MARS (Multi-interface Advection and Reconstruction Solver) method for volume tracking, was employed as a solver of the governing equations of fluids. The phase change rate on the surfaces between the multi-species gas and single-species liquid was calculated. To investigate the ignition process and flame holding mechanism, chemical reaction equations were solved with the detailed chemical mechanism of oxygen and hydrogen. Results suggested that this numerical approach can be a powerful method that provides the information on ignition, breakup and atomization of LOX core, and flame holding at the steady state of LOX/GH2 coaxial combustion at subcritical pressures., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630031027, レポート番号: JAXA-SP-16-007},
 pages = {195--199},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {界面捕獲法を用いた液体ロケットエンジン亜臨界圧燃焼流解析},
 volume = {JAXA-SP-16-007},
 year = {2016}
}