| Summary: | 碩士 === 國立成功大學 === 航空太空工程學系 === 88 === The study applies a Navier-Stokes solver to probe the characteristics of flow of aerodynamics of a NACA0012 airfoil. The solver uses a third-order upwind finite-volume method and modified Osher-Chakravarthy method. The method also uses an implicit residual smoothing to speed up the computational speed. We calculate three different kind of flow such as laminar、turbulent、transition flows and investigate the aerodynamics of the airfoil. For laminar Flow, we can find that different Reynolds number influences the vortex shedding from an airfoil. When the Reynolds number is lower, the flow tends to be steady. For turbulent flow, the solver adopts Baldwin-Lomax turbulent model. For transition flow, the Chen-Thyson transition length model is used to predict the length of the transitional region. The numerical results are compared with experimental.
Keyword：Finite Volume Method、Laminar Flow、Turbulent Flow、Transition Flow、Angle of Attack
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