@inproceedings{oai:jaxa.repo.nii.ac.jp:00005967,
 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2006論文集, JAXA Special Publication: Proceedings of Aerospace Numerical Simulation Symposium 2006},
 month = {Dec},
 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 Soave-Redlich-Kwong equation of state. Thermodynamic and transport properties are evaluated based on departure functions and the corresponding state principle. A fine mesh system with minimum mesh spacing of 1 micrometer is employed to resolve a thin reaction layer under high pressure environment. The present simulation has succeeded to capture the unsteady flame with very thin reaction layer at supercritical pressure. By the analysis of the simulated flame, fundamental features of the LOX/GH2 (Liquid Oxygen/Gaseous Hydrogen) flame are clarified. 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, and no local extinction is observed during the simulation., 資料番号: AA0063154023, レポート番号: JAXA-SP-06-010},
 pages = {125--130},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {ロケットエンジン燃焼関連シミュレーション},
 volume = {JAXA-SP-06-010},
 year = {2006}
}