Experimental and Numerical Investigation on the Flow Near the Leading-Edge of Controlled Diffusion Airfoil

A regional sudden expansion and subsequently compression has a significant influence on boundary development when flow around the leading-edge of Controlled Diffusion Airfoil. The impact of leading-edge curvature is particularly outstanding, a favorable leading-edge curvature can improve the negative effect of regional ambient flow on leading-edge boundary layer development. Surface static pressure and Particle Image Velocimetry were deployed on a cascade to measure the flow near the leading-edge of controlled diffusion airfoil. Experimental and numerical result evince that the spike of continue curvature leading-edge is smaller than which of circle/ellipse leading-edge geometry; the boundary layer thickness development downstream the arc at leading-edge where got by PIV has a close connection with leading-edge spike. Leading-edge geometry and incidence angle will influence the initial state of the boundary layer on the blade surface and then influence airfoil performance.