Two Airfoil Sub-wing Non-stationary Oscillation Ns Equations Of Numerical Simulation

A viscous grid around simple geometries is generated by the elliptic and algebraic method. Base on this initial grid, we can get the unsteady viscous grid by using TFI technique.In this paper the viscous multi-block meshes around complex geometries is generated by line-patched technique. In the test case of oscillating flap the grid deformation technique will be used in the multi-block meshes. For multi-block meshes only the mesh blocks embedding the moving surfaces need to be deformed at each time level. In some cases, additional blocks, not directly adjacent to the moving surfaces, may be deformed in order to obtain smoother grids after deformation.The steady and unsteady viscous flow solvers based on cell-centered finite volume method, and dual method with Runge-Kutte scheme as inner iteration scheme have been development in this dissertation. In dual time method, there are real time and the pseudo-time, at each real time step marches the solution in a pseudo-time to steady state through an explicit time marching scheme, and the equation have two-order accuracy in time. We can make the solver more laconic and spend less time to get the numerical results.Due to the characteristics of the multi-block solving strategy, the data storage and transporting is discussed in this paper. The block calculation will be the lowest level. The calculated results have demonstrated that this strategy is feasibility.To confirm the validity, effectively and reliability of developed flow solver, some test cases for NACA0012 airfoil are performed. Calculations are coincided with experimental result. It has demonstrated that the present method is accuracy and reliability.Through the numerical simulations of steady/unsteady flow for GA(W)-1 airfoil, we have shown that the multi-block solving method is credible. Several demonstrated cases for GA(W)-1 airfoil are presented...