Abstract: The pressure distribution,aerodynamics and PIV velocity fields of a NACA23012 airfoil mounted with a rearward Mini-TED captured in a low speed wind tunnel tests are intro-duced and compared with experimental results of a NACA23012 prototype airfoil in this paper,in order to investigate the influence of the Mini-TED to the flow field and aerodynamics loads of the airfoil.The Reynolds number is 1.3×10 5 based upon the chord length of the airfoil.The pressure distribution on the airfoil is measured using the pressure tubes and pressure transducers,and then the results are integrated to obtain the lift force and pressure drag acting on the airfoil.The total drag is measured using the comb of stagnation pressure based on the momentum theorem. The velocity fields around the airfoil are captured by a PIV system.The rearward Mini-TED in-duces changes to the flow velocity around the airfoil and the wake flow structure,which leads to the variation of the pressure distribution on the suction and pressure surfaces and the increase of both the lift and pressure drag.The position of the front stagnation point of the airfoil with a Mini-TED shifts downstream slightly compared with that of the NACA23012 prototype airfoil, which consequently leads to the increase of the flow velocity on the suction surface and the sup-pression of the flow separation near the trailing edge.