吸い込みによる後退翼面上の境界層遷移の制御 Control of Boundary Layer Transition on a Swept Wing by Suction

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The behavior of three-dimensional boundary layer on swept wings is an important research subject for the future high-speed airplane. The purpose of the present paper is to study controllability of boundary layer transition by suction. Experiments are done by using a closed circuit wind tunnel at Tokai University. The swept wing model with a latch for variable sweep angle at a root is mounted vertically in the 1.5m×1.0m test section. Suction is applied through the perforated surface, and flow velocity of the suction is variable. Two velocity components measured by the twodimensional hot wire anemometer with computer controlled three-dimensional traverse system. At various sweep angles, the velocity inside the boundary layer is measured, and the data are investigated to obtain the relation between the sweep angle and the effect of suction.

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 48(563), 393-398, 2000-12-05 

    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)
    10004831748
  • 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
    5614320
  • 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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