@inproceedings{oai:jaxa.repo.nii.ac.jp:00038091,
 author = {小寺, 正敏 and 須浪, 徹治 and 中橋, 和博 and Kodera, Masatoshi and Sunami, Tetsuji and Nakahashi, Kazuhiro},
 book = {航空宇宙技術研究所特別資料: 航空宇宙数値シミュレーション技術シンポジウム2001論文集, Special Publication of National Aerospace Laboratory: Proceedings of Aerospace Numerical Simulation Symposium 2001},
 month = {Jan},
 note = {In this study, a numerical analysis of combusting flows was made on the scramjet engine which has been tested at Ramjet Engine Test Facility (RJTF) of National Aerospace Laboratory of Japan. The main purpose is to numerically investigate the physical structures of internal combusting flows of the engine closely related to the engine working characteristics at Mach 8 flight condition. The numerical method on unstructured hybrid grid, which solved the Navier-Stokes equations and species conservation equations, based on finite volume cell vortex scheme and the LU-SGS plus diagonal point implicit time integration algorithm was used. The obtained numerical results were carefully compared with the real data obtained by the RJTF firing tests and showed good agreement with the experiment qualitatively and quantitatively. In this paper, based on this validation, emphasis was placed on the mixing and combustion process of the engine whose working condition changed from a weak combustion to a intensive combustion and a unstart., 資料番号: AA0032819055, レポート番号: NAL SP-53},
 pages = {321--326},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {スクラムジェットエンジンの混合・燃焼過程に関する数値的研究},
 volume = {53},
 year = {2002}
}