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

H. Suito, K. Ishii, K. Kuwahara

Research output: Contribution to conferencePaperpeer-review

10 Citations (Scopus)


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.

Original languageEnglish
Number of pages8
Publication statusPublished - 1995 Jan 1
Externally publishedYes
EventFluid Dynamics Conference, 1995 - San Diego, United States
Duration: 1995 Jun 191995 Jun 22


OtherFluid Dynamics Conference, 1995
Country/TerritoryUnited States
CitySan Diego

ASJC Scopus subject areas

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


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