A novel circulation control technique is proposed to overcome the shortcomings of blowing jet circulation control,which uses the synthetic jet as the actuator and avoids the limitation about air supply requirement.The effectiveness of synthetic jet circulation control to enhance lift of NCCR1510-7067N airfoil is confirmed by solving the 2-D unsteady Reynolds-averaged Navier-Stokes equations.The aerodynamic characteristics and the flow structure(especially close to the trailing edge) of NCCR1510-7067N airfoil at zero angle of attack are also presented to discuss the mechanism of lift enhancement of the airfoil with synthetic jet circulation control.The results indicate that the synthetic jet can effectively delay the separation point on the airfoil trailing edge and increase the circulation and lift of the airfoil by Coanda effect.The numerical simulation results demonstrate that the lift augmentation efficiency with synthetic jet circulation control reaches △CL/Cμ=114 in the present study,which is much higher than the value 12.1 in the case with steady blowing jet circulation control. A novel circulation control technique is proposed to overcome the shortcomings of blowing jet circulation control, which uses the synthetic jet as the actuator and avoids the limitation about air supply requirement. The effectiveness of synthetic jet circulation control to enhance lift of NCCR1510-7067N airfoil is confirmed by solving the 2-D unsteady Reynolds-averaged Navier-Stokes equations. aerodynamic characteristics and the flow structure (especially close to the trailing edge) of NCCR1510-7067N airfoil at zero angle of attack are also presented to discuss the mechanism of lift enhancement of the airfoil with synthetic jet circulation control.The performance that the synthetic jet can effectively delay the separation point on the airfoil trailing edge and increase the circulation and lift of the airfoil by Coanda effect. numerical simulation results demonstrate that the lift augmentation efficiency with synthetic jet circulation control △ CL / Cμ = 114 in the present study, which is much higher than the value 12.1 in the case with steady blowing jet circulation control.