@article{oai:jaxa.repo.nii.ac.jp:00035535,
 author = {河田, 三治 and KAWADA, Sandi},
 issue = {237},
 journal = {東京帝國大學航空研究所報告, Report of Aeronautical Research Institute, Tokyo Imperial University},
 month = {Jul},
 note = {Two aerofoils of 4cm chord were tested in 16×16cm high speed wind tunnel. The upper and lower boundaries of the tunnel were removable, thus both closed- and open-type wind tunnel, were available for the experiment. Especially in the closed-type tunnel very clear photographs of the shock waves were obtained. Two different kinds of shock waves were observed. The principal shock wave is the one perpendicular to the flow and in passings this the velocity jumps from supersonic to subsonic state. The another is smaller oblique shock wave situated in front of the former. The velocity after this wave is still supersonic., 資料番号: SA4148622000},
 pages = {244--264},
 title = {衝撃波の生成に關する實驗},
 volume = {18},
 year = {1942}
}