NACA-0012 airfoil with deploying spoiler

Software used: Process of spoiler deviation is being modeling using method of viscous vortex domains (VVD). Re = 40 000. Spoiler size is 10% of chord, spoiler’s trailing edge is 20% far from airfoil’s trailing edge. Angle of attack = 0. Equations: Navier-Stokes; BC: no-slip at the surface, no-perturbations at infinity Please do not hesitate to contact me for any questions.