Abstract
Flow simulations around an airfoil (NACA0012) using Lattice Boltzmann Method (LBM) are performed in this paper. Originally, LBM is an incompressible flow solver on orthogonal coordinates. However, in order to resolve the boundary layer of the airfoil accurately, the algorithm is extended to generalized coordinates. Also, suitable wall boundary condition is introduced for generalized coordinates. First of all, the present numerical method is validated at relatively small Reynolds number (Re=500). The velocity profile of the boundary layer is compared in detail with the CFL3D results and consistent results are obtained. Second, the present method is combined with the Baldwin-Lomax turbulence model, and results at relatively high Reynolds number (Re=5x10 5 ) are shown. The results are in good agreement with the experimental data. With the same grid resolution, the present method can solve high Reynolds
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