@inproceedings{oai:jaxa.repo.nii.ac.jp:00004716,
 author = {溝渕, 泰寛 and 清水, 太郎 and 内藤, 大貴 and Mizobuchi, Yasuhiro and Shimizu, Taro and Naito, Taiki},
 book = {宇宙航空研究開発機構特別資料: 第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 論文集, JAXA Special Publication: Proceedings of 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010},
 month = {Feb},
 note = {第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 (2010年6月24日-25日. 米子コンベンションセンター BiG SHiP), 42nd Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2010 (June 24-25,  2010. Yonago Convention Center BiG SHiP), Yonago, Tottori Japan, A combustion flow in a model combustor equipped with a single injector located at a non-center position of the face plate is numerically simulated to investigate the combustion oscillation driving term, so called 'Rayleigh Index term' which plays a key role when we estimate the combustion stability of rocket engine combustors. The simulation reproduces the unsteady but stabilized flame behavior and reveals the flame stabilization mechanism. The critical combustion oscillation mode, T-mode, is numerically captured and the Rayleigh Index term resulting from the T-mode oscillation is evaluated. An attempt of the response analysis of acoustic/flame interaction is made by forcing pressure fluctuations to show its possibility and availability toward the construction of the combustion stability estimation tool., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0064967009, レポート番号: JAXA-SP-10-012},
 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器安定性解析に向けた予備的燃焼解析},
 volume = {JAXA-SP-10-012},
 year = {2011}
}