Laminar airfoil modification attaining optimum drag reduction by use of airfoil morphing

Hiroharu Suzuki, Kenichi Rinoie, Asei Tezuka

研究成果: Conference contribution

抄録

In this paper, the effectiveness of morphing a laminar airfoil's leading-edge through deformation in order to reduce the drag at the off-design angle of attack is herein investigated. The configuration of the airfoil was deformed under the structural restriction that the leadingedge is deformed while maintaining the girth of the deformed part and the configuration of the "wing box". The NACA 631-012 laminar airfoil was chosen as the original airfoil. The Reynolds number based on the original airfoil chord, was Rec = 3×106. Aerodynamic characteristics of the original and deformed airfoils have been investigated using a Viscous-Inviscid Interaction method. It is shown that the leadingedge deformation is effective in reducing the drag at the off-design angle of attack, in comparison to the original airfoil. The transition point has been estimated using a numerical method based on a linear stability theory. The deformation is an effective means to move the transition point aft on the airfoil, and the extension of the laminar flow area results in a reduction in the drag at the off-design angle of attack.

本文言語English
ホスト出版物のタイトルICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006
ページ1302-1312
ページ数11
出版ステータスPublished - 2006 12 1
外部発表はい
イベント25th Congress of the International Council of the Aeronautical Sciences 2006 - Hamburg, Germany
継続期間: 2006 9 32006 9 8

出版物シリーズ

名前ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006
2

Conference

Conference25th Congress of the International Council of the Aeronautical Sciences 2006
CountryGermany
CityHamburg
Period06/9/306/9/8

ASJC Scopus subject areas

  • Aerospace Engineering
  • Control and Systems Engineering
  • Electrical and Electronic Engineering
  • Materials Science(all)

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