@article{oai:muroran-it.repo.nii.ac.jp:00008348,
 author = {新井,  隆景 and ARAI, Takakage and 笠原,  次郎 and KASAHARA, Jiro and 小久保, 崇 and KOKUBO, Takashi and 向井, 幸司 and MUKAI, Koji},
 journal = {室蘭工業大学紀要, Memoirs of the Muroran Institute of Technology},
 month = {Nov},
 note = {application/pdf, To investigate the fiow and combustian in a Scrarmjet engine model at about Mach 7 condition a small high enthalpy shock tunnel was used. A couple of wedge was set in the test section as a Scramjet engine intake and combustion chamber model. The compression process used the oblique shock systems, which was generated by vehicle edge (fore-body) and cowl, was observed. H2 and/or C2H2-air mixture gas was injected normally to supersonic cross flow in thc combustion chamber. A self-emission from combustion gas was observed by using a very high-speed video camera (18,000fps) with image intcnsifier. The wal1 static pressure in the combustion chamber was also measured. It was clarified that the wall pressure increased when the supersonic combustion occurred., 小特集 : 「室蘭工大における航空宇宙工学研究の新展開」},
 pages = {77--84},
 title = {小型高エンタルピー衝撃風洞を用いたスクラムジェットエンジンモデル内の超音速燃焼},
 volume = {51},
 year = {2001},
 yomi = {アライ, タカカゲ and カサハラ, ジロウ and コクボ, タカシ and ムカイ, コウジ}
}