@inproceedings{oai:jaxa.repo.nii.ac.jp:00014676,
 author = {瀬崎, 新士 and 中村, 弘明 and 西尾, 正富 and 山本, 行光 and Sezaki, Shinji and Nakamura, Hiroaki and Nishio, Masatomi and Yamamoto, Yukimitsu},
 book = {宇宙航行の力学シンポジウム　平成15年度, Symposium on Flight Mechanics and Astrodynamics 2003},
 month = {May},
 note = {The visualization of flowfield around a winged TSTO (Two Stage To Orbit) launch vehicle model has been carried out using the electrical discharge method. In this report, boundary layers and three-dimensional (lateral and cross-sectional) shock shapes around the model are demonstrated. The existence of a separation shock is confirmed three-dimensionally. The experiments are carried out using a hypersonic gun tunnel, with Mach number of 10 and duration of 10 ms., 資料番号: AA0047120031},
 pages = {119--122},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {有翼TSTO宇宙往還機周りの流れ場の放電発光法による可視化研究},
 year = {2004}
}