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

概要

論文の詳細を見る
To investigate the fiow and combustian in a Scrarmjet engine model at about Mach 7 condition a small highenthalpy shock tunnel was used. A couple of wedge was set in the test section as a Scramjet engine intakeand combustion chamber model. The compression process used the oblique shock systems, which wasgenerated by vehicle edge (fore-body) and cowl, was observed. H2 and/or C2H2-air mixture gas was injectednormally to supersonic cross flow in thc combustion chamber. A self-emission from combustion gas wasobserved by using a very high-speed video camera (18,000fps) with image intcnsifier. The wal1 staticpressure in the combustion chamber was also measured. It was clarified that the wall pressure increased whenthe supersonic combustion occurred.
室蘭工業大学の論文
2001-11-30