[mia_axt88]

I just ran a simple 2d airfoil solution on 0 degrees angle of attack. While Calculating solution the graph seems to keep diverging however no error messages are displayed and no solution appears either.

Assuming that my 4-domain mesh was correct (created in Workbench, on a NACA 4 series custom airfoil, namely NACA 2205), can anyone tell me what is wrong with my Case settings and/or Solution settings??

I tried initializing by both hybrid and standard initialization methods. the graph still appears to be continuously diverging.

For the problem statement of

0 degrees angle of attack
10 m/s freestream velocity
101325 Pa atmospheric pressure
1.4607e-05 m2/s kinematic viscosity
288.16 K temperature
1.225 kg/m3 density:

Solver: Pressure-based (since velocity is very less)
Model: viscous-Inviscid, Energy-Off
Material: Fluid-air --> constant --> 1.225
operating Condition: 101,325 Pa
Boundary Conditions:

Regions far ahead and above of airfoil (also some area far above but behind airfoil) assigned as Velocity-inlet with component x=10 m/s, y=0 m/s
Boundary far behind trailing edge, perpendicular to tail of airfoil assigned Pressure Outlet
Airfoil assigned as Wall

Reference Values: computed from Inlet (the Boundary ahead of Airfoil and above)

Solution Methods
Spatial Discretization--> Pressure: PRESTO!
Spatial Discretization--> Momentum: Second Order Upwind

I chose simple Cl monitor along with residuals. with both methods of initialization at a time. solution keeps diverging but shows no error, just stops after the given iterations.

Can someone help??