デトネーション駆動型衝撃風洞を用いた後ろ向きステップ周りの流れ場に関する実験的研究 Experimental Study on Flow Field behind Backward-Facing Step Using Detonation-Driven Shock Tunnel

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As a research to develop a SCRAM-jet engine is actively conducted, a necessity to produce a high-enthalpy flow in a laboratory is increasing. In order to develop the SCRAM-jet engine, stabilized combustion in a supersonic flow-field should be attained, in which a duration time of flow is extremely short. Therefore, a mixing process of breathed air and fuel, which is injected into supersonic flow-fields is one of the most important problem. Since, the flow inside SCRAM-jet engine has high-enthalpy, an experimental facility is required to produce such high-enthalpy flow-field. In this study, a detonation-driven shock tunnel was built and was used to produce high-enthalpy flow. At first, a performance of this facility was investigated in order to obtain a Tayloring condition. Furthermore, SCRAM-jet combustor model equipped backward-facing step was installed at test section and flow-fields were visualized using color-schlieren technique. The fuel was injected perpendicular to the flow of Mach number three behind step. The height of backward-facing step and injection pressure were changed to investigate effects of the step on a mixing characteristic between air and fuel. The schlieren photograph and pressure histories show that the fuel was ignited behind step and the height of step is important factor to ignite a fuel in a supersonic flow-field.

収録刊行物

  • 日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences

    日本航空宇宙学会論文集 = Journal of the Japan Society for Aeronautical and Space Sciences 52(608), 385-392, 2004-09-05

    一般社団法人 日本航空宇宙学会

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各種コード

  • NII論文ID(NAID)
    10013578099
  • NII書誌ID(NCID)
    AA11307372
  • 本文言語コード
    JPN
  • 資料種別
    ART
  • ISSN
    13446460
  • NDL 記事登録ID
    7093178
  • NDL 雑誌分類
    ZN25(科学技術--運輸工学--航空機・ロケット)
  • NDL 請求記号
    Z74-B503
  • データ提供元
    CJP書誌  CJP引用  NDL  J-STAGE 
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