[obdwinston]

Good day All,

I have coded a basic viscous panel method that solves the integral boundary layer equations on an airfoil. It uses a linear vortex panel method to first generate the inviscid flow field, and then uses Thwaites' and Head's methods for laminar and turbulent boundary layers respectively.

The code seems to be producing reasonable results that are surprisingly close to experimental data. You can view the full details of the code, verification, and theory in my GitHub here.

HOWEVER, the big issue that I am facing is that I am having some spurious oscillations towards the trailing edge. I believe it has something to do with flow separation there that is not accounted for, which I did trim off the last few control points at the trailing edge when running the boundary layer solver. If not, literally ANY flow will be separated at the trailing edge, and the program exits since the boundary layer equations fail.

Of note, if you see my GitHub, the oscillations are not shown in the graphs because I omitted them with some cutoff index on the solution vector.

Just trying my luck here to see if anyone knows what I'm referring to and hopefully provide some useful help/resources

Thanks!