Study of Delay of Flow Separation with Moving Surface Control on A Cambered Aerofoil

Abstract

This study investigates the aerodynamic performance enhancement of the NACA 2412 airfoil newlineusing Leading Edge Rotating Cylinders (LERCs) and Moving Panels (MPs) as active flow newlinecontrol mechanisms. While previous research has focused on symmetrical airfoils, their effects newlineon cambered airfoils remain less explored. To address this gap, this study evaluates their newlineaerodynamic impact on NACA 2412, a widely used cambered airfoil representing typical wing newlinesections. newlineComputational Fluid Dynamics (CFD) simulations using the Transition SST turbulence model newlineassess the effects of Cylinder Speed Ratios (CSR) and panel speeds across different Angles of newlineAttack (AOA). The results show that LERCs significantly enhance suction at the leading edge, newlineincreasing lift coefficients (Cl) and delaying stall onset. Larger cylinders provide better flow newlinecontrol, with CSR = 3 shifting flow separation further downstream. The pressure coefficient newline(Cp) distribution confirms stronger suction effects, improving lift. Moving panels, particularly newlineat 0.2C, prove more effective in reducing drag and increasing the L/D ratio, minimizing newlineaerodynamic losses newline