液体窒素フラッシング型低温風洞による後向きステップ流れに関する研究 Study on Backward-Facing Step Flow and Performance of Cryogenic Wind Tunnel Driven by Flashing Liquid Nitrogen

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The experimental study has been conducted to estimate the performance of a cryogenic wind tunnel by using flashing liquid nitrogen and the location of reattachment at the downstream of the backward-facing step. Total and static pressure and temperature of the flow in the test section are measured to calculate flow the Mach number and Reynolds number. Flow visualization by color-schlieren method was also performed. Liquefied nitrogen at a pressure of 700kPa produced the uniform flow, of which the Mach number and total pressure ranges were 0.08 to 0.8, and 20 to 200kPa, respectively. The Reynolds number based on the step height (5mm) ranged from 0.15×10<SUP>5</SUP> to 0.44×10<SUP>5</SUP>, and the duration of stable operation was limited to 0.4–0.8 seconds in our configuration. The results indicated that the prediction by FFT analysis to the reattachment location over the backward-facing step was good agreement with that of their static pressure distributions and visualization results.

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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 52(604), 203-209, 2004-05-05

    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)
    10012934620
  • 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
    6965463
  • 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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