分布式粗糙前缘对NACA0012翼型失速特性的影响

The influence of the distributed leading-edge roughness on the stall characteristics of NACA0012 airfoil is analyzed in full turbulence flow or transition flow. The Menter shear-stress transport model and the γ-Re_{θ t} (Re_{θ t} is transition momentum-thickness Reynolds number, γ is intermittency)transition model are used to simulate the flow around the airfoil by coupling the roughness model and the roughness amplification factor transport equation respectively. The airfoil stall characteristics and the pre-stall boundary layer development are analyzed. The results show that the trailing-edge stall occurs for the NACA0012 airfoil in full turbulence flow, and the stall characteristic is not changed by the leading-edge roughness. The maximum lift coefficients are significantly decreased with the leading-edge roughness at a lower angle of attack. In transition flow, the leading-edge roughness inhibits the formation of leading edge laminar separation bubbles, and the stall characteristic of airfoil is changed from leading-edge stall to trailing-edge stall. The maximum lift coefficient is significantly increased with the leading-edge roughness at a higher angle of attack.