@inproceedings{oai:jaxa.repo.nii.ac.jp:00048390,
 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: 第53回流体力学講演会/第39回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium},
 month = {Feb},
 note = {第53回流体力学講演会/第39回航空宇宙数値シミュレーション技術シンポジウム (2021年6月30日-7月2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), The 53rd Fluid Dynamics Conference / the 39th Aerospace Numerical Simulation Symposium (June 30 - July 2, 2021. 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 others. 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 top 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 the influence of cowl and strut shock waves on the fuel distribution. In this paper the authors describe results of combustion calculation to compare with the test result. It is found that a flow separation occurs in the corner of internal flow, and that the separation causes inclined shock wave to promote the combustion., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA2130027017, レポート番号: JAXA-SP-21-008},
 pages = {193--200},
 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: 性能を左右する内部流剥離の範囲},
 volume = {JAXA-SP-21-008},
 year = {2022}
}