@inproceedings{oai:jaxa.repo.nii.ac.jp:00006143,
 author = {松山, 新吾 and 新城, 淳史 and 溝渕, 泰寛 and 小川, 哲 and Matsuyama, Shingo and Shinjo, Junji and Mizobuchi, Yasuhiro and Ogawa, Satoru},
 book = {宇宙航空研究開発機構特別資料: 航空宇宙数値シミュレーション技術シンポジウム2005論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2005},
 month = {Feb},
 note = {Numerical simulation of liquid oxygen/gaseous hydrogen rocket engine combustor is conducted to investigate the flame structure under supercritical pressure. A preliminary result by an axisymmetric numerical simulation with detailed chemistry is shown for a single shear coaxial injector element which follows the experiment by Mayer and Tamura. A real gas effect under supercritical pressure is accounted for by van der Waals equation of state. A fine mesh system with minimum mesh spacing of 5 micrometers is employed to resolve a thin reaction layer under high pressure environment. A stable flame, though unsteady, is obtained by the present simulation. Fundamental features of the flame are clarified by a brief and short-term (for 0.8 ms) observation of the simulated result. Small eddies, which are generated intermittently at the upper corner of the LOX post tip, interact and coalescence with their neighboring eddies while convecting downstream. A recirculation zone near the LOX post tip drives the GH2 flow toward the LOX stream, which anchors the flame and results in a stationary combustion. The flame edge attaches to the LOX post tip and non-premixed combustion occurs. The flame thickness is less than 0.1 mm. No local extinction is observed during the simulation. The present simulation has succeeded to capture the unsteady flame with very thin reaction layer at supercritical pressure., 資料番号: AA0049212010, レポート番号: JAXA-SP-05-017},
 pages = {65--70},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {ロケットエンジン同軸型噴射器まわりの燃焼シミュレーション},
 volume = {JAXA-SP-05-017},
 year = {2006}
}