@article{oai:muroran-it.repo.nii.ac.jp:00008055,
 author = {杉山,  弘 and SUGIYAMA, Hiromu and 武田, 英樹 and TAKEDA, Hideki and 張, 堅平 and ZHANG, Jianping and 関山, 雅人 and SEKIYAMA, Masato},
 journal = {室蘭工業大学研究報告. 理工編, Memoirs of the Muroran Institute of Technology. Science and engineering},
 month = {Nov},
 note = {application/pdf, When a supersonic flow is decelerated to subsonic flow in a duct, a series of plane or lambda shocks, known as a pseudo-shock wave, is produced as the result of shock wave-turbulent boundary layer interaction. This paper describes an experimental study on the locations and shapes of pseudo-shock waves in straight rectangular ducts when the flows are choked at the duct exits. The experiment was done for Mach number at the duct entrance M∞ from 1.72 to 1.88 and for duct length L/D = 13.8~23.6, where L is the length of the duct and D (= 50mm) the width of the duct. It is shown that the locations of pseudo-shock waves move in a downstream direction with decreasing L/D and increasing M∞. As the locations of pseudo-shock waves move in a down-stream direction, the shapes of pseudo-shock waves change from λ -type to X-type. It is also shown that the location of the pseudo-shock wave in a duct can be predicted by the theory of the Fanno flow with normal shock wave when the flow is choked at the duct exit.},
 pages = {229--238},
 title = {擬似衝撃波に関する研究 (第1報, 直管路内の擬似衝撃波の発生位置と形状)},
 volume = {36},
 year = {1986},
 yomi = {スギヤマ, ヒロム and タケダ, ヒデキ and セキヤマ, マサト}
}