Stability of periodic oscillation around the trailing edge of NACA0012 airfoil

Asei Tezuka*

*この研究の対応する著者

研究成果: Conference contribution

抄録

The performance of the NACA0012 airfoil deteriorates with decreasing Reynolds number owing to the flow separation at the trailing edge. In the wake region, an unstable fluctuation with a discrete frequency, known as trailing edge noise, is observed. It has become controversial whether or not the feedback mechanism between the oscillation of the trailing edge separation and the wake oscillation is actually occurring. The flow at low Reynolds number exhibits a periodic oscillation around the trailing edge of the NACA0012 airfoil. In such a case, the structure of the velocity field changes with the phase in a complicated manner. In order to explore problems regarding unsteady aerodynamic phenomena, comprehension of the flowfield structure is necessary. In addition to the experiment and the numerical computation of the Navier-Stokes Equations (CFD), the theoretical approach from the viewpoint of stability analysis will contribute to understanding the mechanism of such problems. For the purpose of discussing the trailing edge noise, this paper studies the stability of the NACA0012 airfoil using the concept of global linear stability analysis.

本文言語English
ホスト出版物のタイトル6th AIAA Theoretical Fluid Mechanics Conference
出版社American Institute of Aeronautics and Astronautics Inc.
ISBN(印刷版)9781624101441
DOI
出版ステータスPublished - 2011
イベント6th AIAA Theoretical Fluid Mechanics Conference - Honolulu, HI, United States
継続期間: 2011 6 272011 6 30

出版物シリーズ

名前6th AIAA Theoretical Fluid Mechanics Conference

Conference

Conference6th AIAA Theoretical Fluid Mechanics Conference
国/地域United States
CityHonolulu, HI
Period11/6/2711/6/30

ASJC Scopus subject areas

  • 流体および伝熱

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