로터 정지비행 점성유동 해석을 위한 비정렬 격자 기법Viscous Flow Simulation of Rotor Aerodynamics in Hover Using Unstructured Meshes

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A three-dimensional viscous flow solver is developed for the prediction of aerodynamic behavior of hovering helicopter rotor blades using an unstructured mesh methodology. The flow solver utilizes a cell-centered finite-volume scheme that is based on the Roe`s flux-difference splitting and an implicit Jacobi/Gauss-Seidel time integration. The effect of turbulence is estimated by the Spalart-Allmaras one-equation model coupled with a wall function boundary condition. A solution-adaptive mesh refinement technique is adopted to capture the tip vortex. Calculations are performed for non-lifting and lifting rotor cases. Comparison of the inviscid and viscous results indicates that inclusion of viscosity significantly affects the surface pressures and the blade airloads for a lifting rotor at transonic tip speed. Good agreements are obtained between the numerical result and the experiment for both the blade loading and the tip vortex behavior.
Publisher
한국항공우주학회
Issue Date
2001-12
Language
Korean
Citation

한국항공우주학회지, v.29, no.8, pp.37 - 44

ISSN
1225-1348
URI
http://hdl.handle.net/10203/81185
Appears in Collection
AE-Journal Papers(저널논문)
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