スクラムジェットエンジンのマッハ6燃焼試験 -ストラットと分離部の効果について- Mach 6 Combustion Tests of a Scramjet Engine -Effect of Strut and Isolator-

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The main purposes of this study are to investigate the effect of strut configurations and isolator length within the engine on the engine performance at Mach 6 condition, and to determine performance of the engine by gas sampling at the exit plane. The sub-scale scramjet engine had an overall length of 2, 100mm, height of 250mm and width of 200mm and was tested at the RamJet engine Test Facility (RJTF) of the Kakuda Research Center, NAL. In the tests were ompared the effects of strut configurations in an engine with a 200-mm long isolator on the engine performance. The thrust as measured along the fuel flow rate, and the fuel distribution at the engine exit plane was measured by means of gas ampling. It was found that the strut configuration had an effect on the thrust performance, that the 200mm-long isolator as effective in preventing combustor/inlet interaction in the engine with full-height strut, and that the fuel distribution in he engine was not uniform which affected the thrust performance. The maximum thrust obtained was 1620 N at the fuel low rate of 70g/s (the bulk equivalence ratio of 0.4).

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 47(549), 374-382, 1999-10 

    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)
    10002723439
  • 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
    4885212
  • 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  NDL  J-STAGE 
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