Why my 3d panel method code for a NACA 0012 airfoil at zero AOA works, but at 5 degree of AOA fails?

Hi. I have written my own 3d panel method code in MATLAB. it could calculate correct pressure coefficients of a NACA0012 airfoil at zero AoA, but fails to get correct result at 5 degree of AOA,...

07 July 2019 9,487 3 View