PIV study of flow around unsteady airfoil with dynamic trailing-edge flap deflection

摘要: The flow around an oscillating NACA 0015 airfoil with prescheduled trailing-edge flap motion control was investigated by using particle image velocimetry (PIV). Aerodynamic load coefficients, obtained via surface pressure measurements, were also acquired to supplement the PIV results. results demonstrate that upward deflections led improved negative peak pitching moment coefficient C m,peak, mainly as a consequence of increased suction on lower flap. behavior leading-edge vortex (LEV) largely unaffected. Its strength was, however, reduced slightly compared uncontrolled airfoil. No observed. For downward deflection, LEV found be increased. A favorable increase in l,max, flap-induced positive camber effects, accompanied detrimental nose-down due large flap,