Global stability analysis of attached or separated flows over a NACA0012 airfoil

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

2 Citations (Scopus)

Abstract

The stability of a non-parallel flowfield over an airfoil has been investigated by applying a two-dimensional global (non-parallel) linear stability analysis. In this study, Chiba's method, which is a numerical method for the global linear stability analysis, was improved in order to study the stability of the time-averaged flowfield of CFD results. In a laminar separation bubble formed on the airfoil, a sequence of vortices is experimentally observed, which is generated by Kelvin-Helmholtz instability. By applying the stability analysis, we can examine the mode such as an oscillatory phenomenon that is generated by the instability of the flowfield. At higher angles of attack, a separated flow is observed at the leading edge of the airfoil, which corresponds to the stall condition of the airfoil. The results of the global stability analysis at high angles of attack demonstrate the mode which causes the separation at the leading edge of the airfoil. In this paper, the mode of Kelvin-Helmholtz instability and the mode which causes the stall condition of flowfield are presented.

Original languageEnglish
Title of host publicationCollection of Technical Papers - 44th AIAA Aerospace Sciences Meeting
Pages15798-15814
Number of pages17
Volume21
Publication statusPublished - 2006
Externally publishedYes
Event44th AIAA Aerospace Sciences Meeting 2006 - Reno, NV
Duration: 2006 Jan 92006 Jan 12

Other

Other44th AIAA Aerospace Sciences Meeting 2006
CityReno, NV
Period06/1/906/1/12

Fingerprint

separated flow
airfoils
Airfoils
stability analysis
Kelvin-Helmholtz instability
Linear stability analysis
angle of attack
Angle of attack
leading edges
numerical method
vortex
bubble
causes
charge flow devices
Numerical methods
Computational fluid dynamics
Vortex flow
bubbles
vortices

ASJC Scopus subject areas

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Tezuka, A. (2006). Global stability analysis of attached or separated flows over a NACA0012 airfoil. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting (Vol. 21, pp. 15798-15814)

Global stability analysis of attached or separated flows over a NACA0012 airfoil. / Tezuka, Asei.

Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 21 2006. p. 15798-15814.

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

Tezuka, A 2006, Global stability analysis of attached or separated flows over a NACA0012 airfoil. in Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. vol. 21, pp. 15798-15814, 44th AIAA Aerospace Sciences Meeting 2006, Reno, NV, 06/1/9.
Tezuka A. Global stability analysis of attached or separated flows over a NACA0012 airfoil. In Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 21. 2006. p. 15798-15814
Tezuka, Asei. / Global stability analysis of attached or separated flows over a NACA0012 airfoil. Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting. Vol. 21 2006. pp. 15798-15814
@inproceedings{47bdeb74fd034e0a9c978b4cf587c9d0,
title = "Global stability analysis of attached or separated flows over a NACA0012 airfoil",
abstract = "The stability of a non-parallel flowfield over an airfoil has been investigated by applying a two-dimensional global (non-parallel) linear stability analysis. In this study, Chiba's method, which is a numerical method for the global linear stability analysis, was improved in order to study the stability of the time-averaged flowfield of CFD results. In a laminar separation bubble formed on the airfoil, a sequence of vortices is experimentally observed, which is generated by Kelvin-Helmholtz instability. By applying the stability analysis, we can examine the mode such as an oscillatory phenomenon that is generated by the instability of the flowfield. At higher angles of attack, a separated flow is observed at the leading edge of the airfoil, which corresponds to the stall condition of the airfoil. The results of the global stability analysis at high angles of attack demonstrate the mode which causes the separation at the leading edge of the airfoil. In this paper, the mode of Kelvin-Helmholtz instability and the mode which causes the stall condition of flowfield are presented.",
author = "Asei Tezuka",
year = "2006",
language = "English",
isbn = "1563478072",
volume = "21",
pages = "15798--15814",
booktitle = "Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting",

}

TY - GEN

T1 - Global stability analysis of attached or separated flows over a NACA0012 airfoil

AU - Tezuka, Asei

PY - 2006

Y1 - 2006

N2 - The stability of a non-parallel flowfield over an airfoil has been investigated by applying a two-dimensional global (non-parallel) linear stability analysis. In this study, Chiba's method, which is a numerical method for the global linear stability analysis, was improved in order to study the stability of the time-averaged flowfield of CFD results. In a laminar separation bubble formed on the airfoil, a sequence of vortices is experimentally observed, which is generated by Kelvin-Helmholtz instability. By applying the stability analysis, we can examine the mode such as an oscillatory phenomenon that is generated by the instability of the flowfield. At higher angles of attack, a separated flow is observed at the leading edge of the airfoil, which corresponds to the stall condition of the airfoil. The results of the global stability analysis at high angles of attack demonstrate the mode which causes the separation at the leading edge of the airfoil. In this paper, the mode of Kelvin-Helmholtz instability and the mode which causes the stall condition of flowfield are presented.

AB - The stability of a non-parallel flowfield over an airfoil has been investigated by applying a two-dimensional global (non-parallel) linear stability analysis. In this study, Chiba's method, which is a numerical method for the global linear stability analysis, was improved in order to study the stability of the time-averaged flowfield of CFD results. In a laminar separation bubble formed on the airfoil, a sequence of vortices is experimentally observed, which is generated by Kelvin-Helmholtz instability. By applying the stability analysis, we can examine the mode such as an oscillatory phenomenon that is generated by the instability of the flowfield. At higher angles of attack, a separated flow is observed at the leading edge of the airfoil, which corresponds to the stall condition of the airfoil. The results of the global stability analysis at high angles of attack demonstrate the mode which causes the separation at the leading edge of the airfoil. In this paper, the mode of Kelvin-Helmholtz instability and the mode which causes the stall condition of flowfield are presented.

UR - http://www.scopus.com/inward/record.url?scp=34250755389&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=34250755389&partnerID=8YFLogxK

M3 - Conference contribution

AN - SCOPUS:34250755389

SN - 1563478072

SN - 9781563478079

VL - 21

SP - 15798

EP - 15814

BT - Collection of Technical Papers - 44th AIAA Aerospace Sciences Meeting

ER -