보존적 중첩격자기법을 이용한 동적 플랩의 천이적 공력거동에 관한 수치적 연구

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Transient aerodynamic response of an airfoil to a moving plane-flap is numerically investigated using the two-dimensional Euler equations with conservative Chimera grid method. A body moving relative to a stationary grid is treated by an overset grid bounded by a 'Dynamic Domain Dividing Line' which has an advantage for constructing a well-defined hole-cutting boundary. A conservative Chimera grid method with the dynamic domain-dividing line technique is applied and validated by solving the flowfield around a circular cylinder moving supersonic speed. The unsteady and transient characteristics of the flow solver are also examined by computations of an oscillating airfoil and a ramp pitching airfoil respectively. The transient aerodynamic behavior of an airfoil with a moving plane-flap is analyzed for various flow conditions such as deflecting rate of flap and free stream Mach number.
Publisher
한국전산유체공학회
Issue Date
2000-09
Language
Korean
Citation

한국전산유체공학회지, pp.9 - 19

Citation
Journal of computational fluids engineering v.5 no.2 pp.9-19
ISSN
1598-6071
URI
http://hdl.handle.net/10203/19419
Appears in Collection
AE-Journal Papers(저널논문)
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