@techreport{oai:jaxa.repo.nii.ac.jp:00006245,
 author = {谷, 香一郎 and 苅田, 丈士 and 加藤, 周徳 and 桜中, 登 and 渡辺, 修一 and Tani, Koichiro and Kanda, Takeshi and Kato, Kanenori and Sakuranaka, Noboru and Watanabe, Shuichi},
 month = {Jan},
 note = {A designing concept for the inlet of the combined cycle engine was explored in the current study. The models designed by the concept were tested in several wind tunnels, ranging from subsonic to hypersonic air speed. The experimental results showed the decrease of the pressure drag in sub/transonic regime. In supersonic condition, the new model proved the high starting capability. However, in hypersonic range, the inlets lost more mass flow than expected, due to the skewed shock structure. Further studies will be required to establish optimized geometry of the inlet., 資料番号: AA0049056014, レポート番号: JAXA-SP-05-010},
 title = {静止から極超音速域までの複合エンジンインレット性能改善試験について},
 year = {2006}
}