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

Hiroharu Suzuki, Kenichi Rinoie, Asei Tezuka

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

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.

Original languageEnglish
Title of host publicationICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006
Pages1302-1312
Number of pages11
Volume2
Publication statusPublished - 2006
Externally publishedYes
Event25th Congress of the International Council of the Aeronautical Sciences 2006 - Hamburg
Duration: 2006 Sep 32006 Sep 8

Other

Other25th Congress of the International Council of the Aeronautical Sciences 2006
CityHamburg
Period06/9/306/9/8

Fingerprint

Drag reduction
Airfoils
Angle of attack
Drag
Convergence of numerical methods
Laminar flow
Numerical methods
Aerodynamics
Reynolds number

Keywords

  • Airfoil Morphing
  • Drag Reduction
  • Laminar Airfoil
  • Turbulent Transition

ASJC Scopus subject areas

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

Cite this

Suzuki, H., Rinoie, K., & Tezuka, A. (2006). Laminar airfoil modification attaining optimum drag reduction by use of airfoil morphing. In ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006 (Vol. 2, pp. 1302-1312)

Laminar airfoil modification attaining optimum drag reduction by use of airfoil morphing. / Suzuki, Hiroharu; Rinoie, Kenichi; Tezuka, Asei.

ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006. Vol. 2 2006. p. 1302-1312.

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Suzuki, H, Rinoie, K & Tezuka, A 2006, Laminar airfoil modification attaining optimum drag reduction by use of airfoil morphing. in ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006. vol. 2, pp. 1302-1312, 25th Congress of the International Council of the Aeronautical Sciences 2006, Hamburg, 06/9/3.
Suzuki H, Rinoie K, Tezuka A. Laminar airfoil modification attaining optimum drag reduction by use of airfoil morphing. In ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006. Vol. 2. 2006. p. 1302-1312
Suzuki, Hiroharu ; Rinoie, Kenichi ; Tezuka, Asei. / Laminar airfoil modification attaining optimum drag reduction by use of airfoil morphing. ICAS-Secretariat - 25th Congress of the International Council of the Aeronautical Sciences 2006. Vol. 2 2006. pp. 1302-1312
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