Abstract: The high-lift configuration of aerodynamic standard model can be used in various aspects, such as complex flow mechanism study, CFD software verification, low-speed wind tunnel capability research and aero-acoustic test. In the design process of the high-lift configuration of the civil aircraft aerodynamic standard model CAE-AVM-HL, numerical optimization based on the surrogate model is adopted. The optimization process includes sample establishment, geometry parameterization, surrogate model establishment and genetic algorithm optimization. The final form of the high-lift wing is featured with a variable camber droop-nose leading edge, a leading-edge slat and a single slot trailing-edge flap. The wind tunnel test model of civil aircraft aerodynamic standard model with high lift configuration CAE-AVM-HL was processed by Deharde company in Germany, and was tested in the German-Dutch large low-speed wind tunnel DNW-LLF at Mach number 0.2 and Reynolds number 3 million. The wind tunnel test includes force/pressure/deformation measurement, transition trip effect, silk tuft/oil flow, PIV measurement, etc. In view of the influence of the flow interaction between the droop-nose leading edge and the leading-edge slat, an anti-flow separation design scheme is proposed. Both CFD calculation and wind tunnel test show that the anti-flow separation design scheme alleviates the flow interference. The final measured maximum lift coefficient of the configuration is 2.56 and the stall angle of attack is 19°, which meet the design requirements.