Parametric Study of Transient Spoiler Aerodynamics with Two-Equation Turbulence Models

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The transient response of an airfoil to a rapidly deploying spoiler is numerically investigated using the turbulent compressible Navier-Stokes equations in two dimensions. The algebraic Baldwin-Lomax model, Wilcox k-omega model, and shear stress transport k-omega turbulence models were used to calculate the unsteady separated flow due to the rapid spoiler deployment. The spoiler motion relative to a stationary airfoil is treated using an overset grid bounded by a dynamic domain-dividing line, which has been devised by the authors. The adverse effects of the spoiler influenced by the spoiler location and the hinge gap are expounded. The numerical results are in reasonably good agreement with the existing experimental data.
Publisher
Amer Inst Aeronaut Astronaut
Issue Date
2001-09
Language
English
Article Type
Article; Proceedings Paper
Keywords

AIRFOIL; COMPUTATION; FLOWS

Citation

JOURNAL OF AIRCRAFT, v.38, no.5, pp.888 - 894

ISSN
0021-8669
DOI
10.2514/2.2848
URI
http://hdl.handle.net/10203/93864
Appears in Collection
AE-Journal Papers(저널논문)
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