![]() All surface modification also resulted in a decrease in drag at 15°. The results showed that all surface modifications led to delayed flow separation and flow recirculation. Also, the lift coefficient, drag coefficient and the lift-to-drag performance ratio were computed and analyzed. ![]() ![]() The velocity contours and streamlines were generated. The analysis used the Shear Stress Transport k – ω turbulence model at a varying angle of attack (AOA) from 0 to 15°. A computational fluid dynamics (CFD) analysis was conducted on these models at subsonic flow using Ansys Fluent. Six modified airfoils were designed with dimples and bumps of spherical and pyramidical shapes. In this study, surface features such as dimples and bumps are introduced to the surface of a NACA 0012 airfoil to study their effect on boundary layer separation, particularly at high angles of attack. ![]()
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