718 衝撃風洞を用いたスクラムジェットエンジン内の流れと超音速燃焼(OS7-6 航空宇宙推進(流体,燃焼))(OS7 北海道における航空宇宙工学研究の進展と未来)

概要

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Flow and combustion phenomena in a scramjet engine model were investigated by using a small high enthalpy shock tunnel. At Mach number about 6.5, double wedges were set in the test section as a scramjet engine intake and a combustion chamber model. Schlieren-image visualization and wall static pressure measurements were conducted. The compression process used the oblique shock system, which was generated by vehicle edge (fore-body) and cowl, was observed. H_2 and/or premixed C_2H_2-air mixture was injected normally to the supersonic cross flow in the combustion chamber model. To observe a self-emission from combustion gas, the high-speed video camera (18,000fps) with an image intensifier unit was used. The supersonic combustion in supersonic flowfield in the combustion chamber model was confirmed.
社団法人日本機械学会の論文
2001-09-25