Please I'm using structured C-grid generation to simulate numerically flow about NACA airfoil. My code program diverge after it reachs 10**(-4) between two concequative velocity values.

That's some details of my code program: 2D, incomressible, laminar, viscous flow grid dimension:191x145 streching coeffecients: 0.12, 0.12 Re number: 2x10**3 relaxation parameters for all variables: 0.05 finite volumes method with upwind second order scheem SIMPLER Algorithm

Please i'm ready for more details if you would like help me to run my code.

Hi,

Just try running ur code without the airfoil...just a plane flow..theoretically the solution should not change with time. If u still get an error, i think the probability of finding an error due to the grid (like calculation of angles etc) is more. The other thing i suggest is try a simple test case--a flat plate or flow between parallel plates and see wat happens.

regards,

B787

Thanks verry much for y're interest, I'm runing the code for permanent case and zero angle of attack. But i have a difficulties in imposing boundary conditions in numerical domain

I need only a grid generation soft (free) for simulate a C or O grid about a 2D profile (orthogonal mesh in a computational plane), please if you know some one link send me it.

Thanks

Santiago Argentina

studentfluent.com, click on mesh lib and download all the mesh files you wish for free

u can try ugrid or shore-cfd. one is o-grid, another is c-grid. google them...

thanks Ahmed, I´ll try. Later I`ll talk about.

Bye

thanks zonexo, I´ll try. Later I`ll talk about.

Bye