Inverse Design of a Thick Supercritical Airfoil

この論文にアクセスする

この論文をさがす

著者

抄録

In this paper, a study on designing a thick supercritical airfoil by utilizing Takanashi's inverse design method is discussed. One of the problems to design a thick supercritical airfoil by Takanashi's method is that an oscillation of the geometry may occur during the iteration process. To reduce the oscillation, an airfoil parameterization method is utilized as the smoothing procedure. A guideline to determine the target pressure distribution to realize the thick airfoil is also discussed.

収録刊行物

  • Transactions of the Japan Society for Aeronautical and Space Sciences  

    Transactions of the Japan Society for Aeronautical and Space Sciences 43(140), 61-66, 2000-08-04 

    THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

参考文献:  8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)
    10004532937
  • NII書誌ID(NCID)
    AA0086707X
  • 本文言語コード
    ENG
  • 資料種別
    ART
  • ISSN
    05493811
  • NDL 記事登録ID
    5485796
  • 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
    Z53-M236
  • データ提供元
    CJP書誌  NDL  J-STAGE 
ページトップへ