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

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