## Abstract

The unsteady flow field around an NACA0012 airfoil oscillating in pitch (angle of attack α= α_{0} + α_{1} sin Ωt ) is analyzed numerically at Reynolds number (based on airfoil chord length ) Re=5.0 * 10^{5} 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 * 10^{4} and 4.5 * 10^{4} 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 |
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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 |
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Country/Territory | 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