[scd62]

Hi all,

I'm doing a research project on BEMT theory which utilises airfoil tables (with multiple airfoil polars) as an input to calculate aerodynamics of a propeller. I have been using XFOIL to do this up till now, but I am dealing with very low Re flows (as low as 30-50k) which XFOIL really doesn't seem to like as it produces inaccurate polars.

I'm wondering if anyone has any idea on where to even start for automating a process in ANSYS where I can use an airfoil profile such as NACA4412, and input some ranges of angle of attack and Reynolds number, and have it basically generate an airfoil table of the lift and drag coefficients for each case over the input ranges? I'm sure I could figure out a way to run a single case fine, but I would really need a large range of angle of attacks and Reynolds numbers which would take forever.

Any help or ideas would be super welcomed.
Cheers