Simulation of dynamic stall by multi-directional finite-difference method

H. Suito, K. Ishii, K. Kuwahara

研究成果: Paper査読

7 被引用数 (Scopus)

抄録

The unsteady flow field around an NACA0012 airfoil oscillating in pitch (angle of attack α= α0 + α1 sin Ωt ) is analyzed numerically at Reynolds number (based on airfoil chord length ) Re=5.0 * 105 and nondimensional pitch rate Ω = 0.2 using the two-dimensional incompressible Navier-Stokes equations. To analyze a separating strong shear layer, we use a newly-developed Multi-Directional Finite-Difference Method. Applying this method to the present problem, the process of the dynamic stall is well captured. Before this calculation, some calculations of a flow around an constant-rate pitching airfoil at Re = 1.0 * 104 and 4.5 * 104 were done for validation of the present method. The angle of attack at which big separation ("break away”) ocuurs is in good agreement with experiment, and the sequence of boundary-layer separation is visualized in the form of animation. This result has proved accuracy and reliability of the present method.

本文言語English
ページ1-8
ページ数8
出版ステータスPublished - 1995 1 1
外部発表はい
イベントFluid Dynamics Conference, 1995 - San Diego, United States
継続期間: 1995 6 191995 6 22

Other

OtherFluid Dynamics Conference, 1995
CountryUnited States
CitySan Diego
Period95/6/1995/6/22

ASJC Scopus subject areas

  • Aerospace Engineering
  • Mechanical Engineering
  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology

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