極超音速流中のランプ誘起衝撃波/遷移境界層干渉の実験的研究 An Experimental Study on a Ramp-Induced Shock-Wave/Transitional-Boundary-Layer Interaction in Hypersonic Flow

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An experimental investigation of a shock-wave/transitional-boundary-layer interaction was conducted on a flat plate with an aft-mounted ramp in a hypersonic gun tunnel. Test Mach number was 10, the Reynolds number range Re<SUB>L</SUB> based on the model plate length was from 1.1 to 3.2 × 10<SUP>5</SUP>, the attack angle of the model was zero, and the ramp deflection angle θ<SUB>w</SUB> was varied from 10 to 30deg in increments of 2. The effects of Re<SUB>L</SUB> and θ<SUB>w</SUB> on the characteristics of the interaction region were investigated through both schlieren visualization and heat transfer measurement. The state of reattaching boundary layers were determined from these data. The following is obtained. A model that describes how the upstream influence of a shock-wave/boundary-layer interaction scales with the parameters of the incoming flow agrees with laminar data at small Re<SUB>L</SUB><SUP>-1/8</SUP>Δθ<SUB>w</SUB>, where Δθ<SUB>w</SUB> is the incremental angle after incipient separation. The slope of the characteristic curve of the upstream influence is dependent on the type of the interaction. Re<SUB>L</SUB><SUP>-1/8</SUP> Δθ<SUB>w</SUB> where the deviation from the model occurs and flow unsteadiness appears is found to become small with increasing Re<SUB>L</SUB>.

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  • 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 55(646), 541-545, 2007-11-05 

    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)
    10021152588
  • 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
    9271895
  • 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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