Numerical investigation of parietal pressure distribution on NACA0012 wing controlled by micro-cylindrical rod arranged in tandem

A parametric investigation of the influence a small cylinder on laminar separated boundary layer over NACA0012 wing is performed using numerical simulations. The (γ - Reθ,t) steady RANS transitional model first validated in capturing separation baseline suction surface. effects three rod diameter ratios (d/c = 0.67%, 1.33% and 2%) bubble aerodynamic performances were examined. qualitative analysis flow structures revealed mechanisms control device for aerofoil performance improvements. formation vortices wake exerted considerable LSB size, pressure coefficient streamlines. Particularly, it contributes to eliminate with pronounced decrease 75% by energising shear significant extent, resulting mean drag dropping 73% at 12° incidence, lift enhancement about 23% 15°.