@inproceedings{oai:jaxa.repo.nii.ac.jp:00047337,
 author = {佐藤, 茂 and 福井, 正明 and 宗像, 利彦 and 渡邉, 孝宏 and 髙橋, 正晴 and SATO, Shigeru and FUKUI, Masaaki and MUNAKATA, Toshihiko and WATANABE, Takahiro and TAKAHASHI, Masaharu},
 book = {宇宙航空研究開発機構特別資料: 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2020オンライン論文集, JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online},
 month = {Feb},
 note = {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2020オンライン (2020年9月28日-30日. 日本航空宇宙学会 : 宇宙航空研究開発機構(JAXA)オンライン会議), Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting), Japan Aerospace Exploration Agency has been investigating scramjet engines in Kakuda Space Center using RamJet Engine Test Facility and another facility. The engine tested at the flight condition of Mach 6 showed very steep fuel distribution. The fuel injected from the vertical injector on the side wall stays near the side wall and the tap wall along the engine. The steep fuel distribution is an obstacle for the engine performance completion. In order to solve the problem, the authors are focusing on the cowl shock wave influence having on the fuel distribution. In this paper the authors describe results of fuel distribution derived from combustion calculation to compare with the test result. Some disagreement is found and considered to be caused by capturing flow separation in the calculation, though the separation promotes fuel mixing and combustion. The mixing process is shown., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2030013016, レポート番号: JAXA-SP-20-008},
 pages = {119--128},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {スクラムジェットエンジン性能向上に関する試み: 剥離と燃料当量比分布},
 volume = {JAXA-SP-20-008},
 year = {2021}
}