疑似衝撃波の形成機構に関する研究 A Study on Pseudo-Shock Wave Formation Mechanism

この論文にアクセスする

この論文をさがす

著者

抄録

The characterization of pseudo-shock wave which is made by interaction between a shock wave and boundary layer is important for various aerospace engineering purposes including the isolator in a scram jet engine. In the present paper, two-dimensional numerical simulation was conducted to reveal physically how the shock-boundary layer interaction produces a pseudo-oblique shock wave for a supersonic channel flow with a slender obstacle located at the center downstream. It is found that a high-speed jet against the supersonic main flow which is issued from the attachment point of a shock wave with the channel wall is the main mechanism for the formation of a series of reverse flow regions in the pseudo-shock wave.

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 54(628), 189-195, 2006-05-05 

    一般社団法人 日本航空宇宙学会

参考文献:  10件

参考文献を見るにはログインが必要です。ユーザIDをお持ちでない方は新規登録してください。

各種コード

  • NII論文ID(NAID)
    10018055305
  • 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
    7964329
  • 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 
ページトップへ