[losiola]

Hello Foamers ,
I am making a 2D airfoil simulation using openFoam , i ve followed the wingmotion tutorial to do so .


after the creation of mesh , i ve made ,at first, the simulation using simpleFoam( steady state solver ) and the convergence was really good and also the Cm,Cd,Cl coefficients were good . but once i use the same case using pimpleFoam the solution divergese and the residuals seems to be like stuck at 0.1 for presseure and 0.001 for the velocity .


Do you have any idea about what would the problem be ?!