I am working on 2D, incompressible, laminar viscous flow about an airfoil. I have used 'C grid generation' and finite volumes method with simpler algorithm and upwind second order schem. My code program written in fortran still diverge, perhaps because boundary conditions in calcul domain are not well imposed. Can you help me please to correct my code?

how can I help with the above given information?

Thanks for y're response to help call. Please if y're ready i'll send you my code program with word file of mathematical model and other informations.

check your email,please.

Mister dingxiwang, i h've sent you two messages to y're email, the first contains my code program with a data file for grid generation, and a word file explaining the problem. The second message contains a latest version of my code program. Thanks verry much for y're help

excuse me perhaps i've made an error in y're email address, thats the files please. thanks verry much

Please i've sent the message 'aerodyn3', with three files i've promised. If you h've received there please email me.

Please its the 5th email to you, but i'vent received any answer?

you probléme is the stretching of the gird

Salem Imad, Effectivelly i have a doubt about grid. I'm working with 'C grid', but when i increase the number of grids or the coefficients of stretching the code program dont work. Actually i'm using grid of (191x145) with stretching parameters 0.12 and 0.12, what may i use?

Friend Imad, thanks verry much and probably y're the unic one who understand my problem

Friend Imad, I'vent received an answer from you, is that because the bad formulation of my question about the grid generation i'm using.

Please, if y're ready we can discus in french language.

Thanks

i want to know about the details of the FVM in Airfoil kindly accept my message here and send relevant data for my email id

thank you