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

H. Suito; K. Ishii; K. Kuwahara

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

H. Suito, K. Ishii, K. Kuwahara

Research output: Contribution to conference › Paper › peer-review

Abstract

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 language	English
Pages	1-8
Number of pages	8
Publication status	Published - 1995 Jan 1
Externally published	Yes
Event	Fluid Dynamics Conference, 1995 - San Diego, United States Duration: 1995 Jun 19 → 1995 Jun 22

Other

Other	Fluid Dynamics Conference, 1995
Country	United States
City	San Diego
Period	95/6/19 → 95/6/22

ASJC Scopus subject areas

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

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abstract = "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.",

author = "H. Suito and K. Ishii and K. Kuwahara",

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T1 - Simulation of dynamic stall by multi-directional finite-difference method

AU - Suito, H.

AU - Ishii, K.

AU - Kuwahara, K.

PY - 1995/1/1

Y1 - 1995/1/1

N2 - 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.

AB - 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.

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

Abstract

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ASJC Scopus subject areas

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