In this paper, multigrid techniques together with homotopy method are applied to propose a kind of finite-difference relaxation scheme for 2D steady-state Navier-Stokes equations. The proposed numerical scheme can giv...In this paper, multigrid techniques together with homotopy method are applied to propose a kind of finite-difference relaxation scheme for 2D steady-state Navier-Stokes equations. The proposed numerical scheme can give convergent results for viscous flows with high Reynolds number. As an example, the results of shear-driven cavity flow with high Reynolds number up to 25000 on fine grid 257×257 are given.展开更多
In this paper, the aerodynamic flowfield of a transonic propeller is computed by using the existing code at DLR, named FLOWer which is based on the Jamesons finite volume method and multigrid technique. Several parame...In this paper, the aerodynamic flowfield of a transonic propeller is computed by using the existing code at DLR, named FLOWer which is based on the Jamesons finite volume method and multigrid technique. Several parameters including artificial dissipation coefficients and scaling factor are tested. The computational results are in agreement with experimental data. The calculations obtained are able to capture several important flow features such as the shock waves and blade tip vortices.展开更多
文摘In this paper, multigrid techniques together with homotopy method are applied to propose a kind of finite-difference relaxation scheme for 2D steady-state Navier-Stokes equations. The proposed numerical scheme can give convergent results for viscous flows with high Reynolds number. As an example, the results of shear-driven cavity flow with high Reynolds number up to 25000 on fine grid 257×257 are given.
文摘In this paper, the aerodynamic flowfield of a transonic propeller is computed by using the existing code at DLR, named FLOWer which is based on the Jamesons finite volume method and multigrid technique. Several parameters including artificial dissipation coefficients and scaling factor are tested. The computational results are in agreement with experimental data. The calculations obtained are able to capture several important flow features such as the shock waves and blade tip vortices.
