naca2412 analysis
 

Hi,
I am trying to analyze a naca2412 airfoil in wind-us and trying to plot "lift" residuals using "resplt" but when I do so i get a constant value of zero after almost 30000 iterations. I am using an anngle of attack of 12 degrees and a free stream mach number of 0.2. I am unable to figure out where I am going wrong.

Thanks