[johnsherjy]

Hi

I am trying to simulate flow over 4 airfoil one kept in the wake of another airfoil in 2D case. Rectangular domain is taken as the flow domain with K-omega model with polyhedral mesh.
Chord length c= 0.605m
Top and bottom surface = 5c -(symmetry plane)
inlet velocity =109 m/s
outlet = Pressure outlet
I am not able to get the predicted flow output. After some time, there is zero velocity zones in the domain. I have no clue why is it happening. It would be grateful if anyone could help me figure out the problem. I hereby attach the velocity scalar scene of the flow.
Thank you in advance

[fluid23]

How many iterations? What do your residuals look like? How are you initializing the solution?

You need to provide more info.

[johnsherjy]

time step = 7.989*10^-5
the problem happens after around 0.5sec
the residuals converge upto less than 10^-4