前缘缝翼多目标气动性能优化设计

Leading edge slat can inhibit the flow separation at large angles of attack and effectively improve the aerodynamic performance. Determining the geometry parameters of slat is vital to improve the aerodynamic performance. Therefore, the aerodynamic performance of leading edge slat was optimized based on multi-objective genetic algorithm. NACA 0012 was selected to design the geometry parameters of slats, and the input parameters such as slat width, position and curves degree were defined. The optimized Latin-hypercube method was used for sampling. The sample data were used to establish the input parameters and the surrogate model with lift and drag coefficient as the target parameters to improve the optimization efficiency, and the multi-objective genetic algorithm was used to optimize the target parameters in the glob-al scope. Results indicated the lift coefficient increased obviously with the large curves degree of slat. Leading-edge slat improved the aerodynamic performance by increasing the turbulent kinetic energy of upper wing sur-face and reducing the pressure coefficient of the front edge of the upper wing. After optimization, the maximum lift coefficient of the airfoil with slat was increased by 12.5% and the stall angle of attack was delayed by 5°. It could provide theoretical support for the optimization design of airfoil aerodynamic performance with slat.