Unknown failure solving airfoils
I´m trying to obtain the preassure coeficient of some airfoil designs. After creating the design with Caedium builder, I follow the steps described in the tutorial for a NACA 0012 airfoil in RANS flow.
The problem came when I applied the solver and this message showed up.
volume_32 [www.7383.5] RANS Flow: Failed
Solver singularity: smoothSolver: Solving for epsilon, Initial residual = -1.#IND, Final residual = 1.#QNAN, No Iterations 100"
Please, could someone tell me what I'm doing wrong and how can I solve it?