Flow simulations around an airfoil (NACA0012) using the lattice Boltzmann method (LBM) are performed. Originally, the LBM is an incompressible flow solver on orthogonal coordinates. However, to resolve the boundary layer of the airfoil accurately, the algorithm is extended to generalized coordinates. Also, a suitable wall boundary condition is introduced for generalized coordinates. First, the numerical method is validated at a relatively small Reynolds number (Re = 500). The velocity profile of the boundary layer is compared in detail with the computational fluid dynamics code CFL3D (developed at NASA Langley Research Center) results, and consistent results are obtained. Second, the method is combined with the Baldwin-Lomax turbulence model and results at relatively high Reynolds number (Re 5 x 105) are shown. The results are in good agreement with the experimental data. With the same grid resolution, the method can solve high-Reynolds-number flows as accurately as traditional Navier-Stokes solvers.
Flow simulation around an airfoil by lattice Boltzmann method on generalized coordinates
Simulation der Umströmung eines Tragflügels mit dem Gitter-Boltzmann-Verfahren auf Basis verallgemeinerter Koordinaten
AIAA Journal ; 43 , 9 ; 1968-1973
2005
6 Seiten, 7 Bilder, 2 Tabellen, 10 Quellen
Aufsatz (Zeitschrift)
Englisch
FLOW SIMULATION AROUND AN AIRFOIL USING LATTICE BOLTZMANN METHOD ON GENERALIZED COORDINATES
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