Stability of periodic oscillation around the trailing edge of NACA0012 airfoil

Asei Tezuka*

*Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

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.

Original languageEnglish
Title of host publication6th AIAA Theoretical Fluid Mechanics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781624101441
DOIs
Publication statusPublished - 2011
Event6th AIAA Theoretical Fluid Mechanics Conference - Honolulu, HI, United States
Duration: 2011 Jun 272011 Jun 30

Publication series

Name6th AIAA Theoretical Fluid Mechanics Conference

Conference

Conference6th AIAA Theoretical Fluid Mechanics Conference
Country/TerritoryUnited States
CityHonolulu, HI
Period11/6/2711/6/30

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes

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