@inproceedings{oai:jaxa.repo.nii.ac.jp:00014704,
 author = {中村, 弘明 and 真鍋, 圭司 and 瀬崎, 新士 and 西尾, 正富 and Nakamura, Hiroaki and Manabe, Keiji and Sezaki, Shinji and Nishio, Masatomi},
 book = {宇宙航行の力学シンポジウム　平成14年度, Symposium on Flight Mechanics and Astrodynamics 2002},
 month = {Mar},
 note = {The flowfield analysis around a model of space plane traveling at Mach 10 has been carried out utilizing the Electric Discharge Method and the Finite Element Method (FEM) scheme. The Electric Discharge Method can visualize almost all important hypersonic flowfield phenomena, such as three-dimensional shock shapes, streamlines near wall surface, distant streamlines from wall surface, boundary layers, etc. In this study, the experiments and the numerical simulations were carried out under the conditions the angles of attack were 0 and 10 deg. Furthermore, the experimental results were compared with the numerical ones. In these comparisons, it was found that they were relatively in good agreement., 資料番号: AA0045913017},
 pages = {63--66},
 publisher = {宇宙科学研究所, The Institute of Space and Astronautical Science (ISAS)},
 title = {極超音速飛行するスペースプレーン周りの流れ場の3次元的研究},
 year = {2003}
}