Unsteady flow around airfoil with a rapidly deploying spoiler

Tao Zhou; Chao Yan

Unsteady flow around airfoil with a rapidly deploying spoiler

Tao Zhou^*
, Chao Yan

^*Corresponding author for this work

School of Aeronautic Science and Engineering

Beihang University

Research output: Contribution to journal › Article › peer-review

Abstract

Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated by solving two-dimensional unsteady compressible Navier-Stokes equations. The spoiler moving relative to a stationary airfoil is treated by a dynamic overset grid method. The mechanism of the adverse lift caused by the rapidly deploying spoiler is analyzed. Also, the effects of angle of attack, height of spoiler and rapidly deploying rate on the adverse lift are investigated.

Original language	English
Pages (from-to)	1009-1013+1144
Journal	Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica
Volume	27
Issue number	6
State	Published - Nov 2006

Keywords

CFD
Overset grid
Spoiler
Unsteady

Cite this

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title = "Unsteady flow around airfoil with a rapidly deploying spoiler",

abstract = "Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated by solving two-dimensional unsteady compressible Navier-Stokes equations. The spoiler moving relative to a stationary airfoil is treated by a dynamic overset grid method. The mechanism of the adverse lift caused by the rapidly deploying spoiler is analyzed. Also, the effects of angle of attack, height of spoiler and rapidly deploying rate on the adverse lift are investigated.",

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AU - Yan, Chao

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N2 - Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated by solving two-dimensional unsteady compressible Navier-Stokes equations. The spoiler moving relative to a stationary airfoil is treated by a dynamic overset grid method. The mechanism of the adverse lift caused by the rapidly deploying spoiler is analyzed. Also, the effects of angle of attack, height of spoiler and rapidly deploying rate on the adverse lift are investigated.

AB - Transient aerodynamic response of an airfoil to a rapidly deploying spoiler is numerically investigated by solving two-dimensional unsteady compressible Navier-Stokes equations. The spoiler moving relative to a stationary airfoil is treated by a dynamic overset grid method. The mechanism of the adverse lift caused by the rapidly deploying spoiler is analyzed. Also, the effects of angle of attack, height of spoiler and rapidly deploying rate on the adverse lift are investigated.

KW - CFD

KW - Overset grid

KW - Spoiler

KW - Unsteady

UR - https://www.scopus.com/pages/publications/33846827124

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SN - 1000-6893

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JO - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

JF - Hangkong Xuebao/Acta Aeronautica et Astronautica Sinica

IS - 6

ER -

Unsteady flow around airfoil with a rapidly deploying spoiler

Abstract

Keywords

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