摘要
In the computational fluid dynamics there are three types of body-fitting grid generation method for incompressible viscous flow over an aerofoil, i.e. O-type, C-type and H-type. The numerical solution of H-type grid and a special difference scheme were obtained. In order to prevent the oscillation of pressure, u was defined at the nodes of the mesh, but v and p were defined as staggered grid. Upwind scheme in the convective terms was used and the iteration with success lower relaxation of implicit difference equations were unconditional stability. The method of mass flux correction was introduced with the success in order to accelerate convergence in iteration of velocity and pressure calculation. Numerical results indicate that H-type grid generation is successful to solve problem of external flow and artificial compressity method with correction technique of total mass flux can improve convergence rate.
In the computational fluid dynamics there are three types of body-fitting grid generation method for incompressible viscous flow over an aerofoil, i.e. O-type, C-type and H-type. The numerical solution of H-type grid and a special difference scheme were obtained. In order to prevent the oscillation of pressure, u was defined at the nodes of the mesh, but v and p were defined as staggered grid. Upwind scheme in the convective terms was used and the iteration with success lower relaxation of implicit difference equations were unconditional stability. The method of mass flux correction was introduced with the success in order to accelerate convergence in iteration of velocity and pressure calculation. Numerical results indicate that H-type grid generation is successful to solve problem of external flow and artificial compressity method with correction technique of total mass flux can improve convergence rate.
