@inproceedings{oai:jaxa.repo.nii.ac.jp:00006146,
 author = {高橋, 政浩 and 小寺, 正敏 and 小室, 智幸 and 佐藤, 和雄 and 伊藤, 勝宏 and Takahashi, Masahiro and Kodera, Masatoshi and Komuro, Tomoyuki and Sato, Kazuo and Ito, Katsuhiro},
 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 = {To investigate hypervelocity scramjet characteristics, numerical simulation was applied to combusting flows in a M12-02 HM scramjet engine at a free-stream stagnation enthalpy of 5 MJ/kg and 7 MJ/kg, which corresponds to the flight Mach number condition of 10 and 12. The numerical results were compared with the experimental results obtained by using a large free-piston shock tunnel to verify the numerical procedure. Good agreement was obtained between the numerical and experimental results of the wall pressure distribution. The results gave detailed information on the ignition process in the combustor. To investigate influence of the uncertainty in the test flow composition on the combustion process in the engine, numerical results computed assuming the free-stream condition with and without a small amount of atomic oxygen were compared. At 5 MJ/kg condition, existence of atomic oxygen in the free-stream affected ignition process and better agreement with the experimental results was obtained in the case of the free-stream condition without atomic oxygen than in the case with atomic oxygen. The numerical simulation showed that the combustor gas temperature exceeded 2,600 K at near the combustor exit and loss in the net combustion heat release due to thermal dissociation of the combusting gas was still one of major causes to drop the combustor performance., 資料番号: AA0049212013, レポート番号: JAXA-SP-05-017},
 pages = {82--87},
 publisher = {宇宙航空研究開発機構, Japan Aerospace Exploration Agency (JAXA)},
 title = {マッハ10以上の超高速域スクラムジェット作動特性に関する数値解析},
 volume = {JAXA-SP-05-017},
 year = {2006}
}