Abstract
Turbulent flow around wings are simulated by solving the three-dimensional Navier-Stokes equations in hexahedronal computational cells. Turbulent flow is described by an algebraic eddy viscosity model. Boundary-conforming O-O type meshes are generated by the transfinite interpolation method. The finite-volume technique is employed for spatial discretization using two cells in each computational coordinate direction, one more than the conventional approach to evaluate the viscous fluxes. An explicit three-stage Runge-Kutta scheme is used for the time integration. The method is applied to compute turbulent transonic flow around the DLR F5 wing, which has been studied extensively both experimentally and numerically in a recent workshop. Our results are compared with those workshop data.
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