Airfoil robust design with uncertainty parameters

A robust design optimization of 2D airfoil with uncertainty of inlet Mach number was presented. Based on NACA0012, a series of geometry as well as boundary parameters were introduced. Three optimization methods, including single-point method, multi-point method as well as robust method, were discussed. Airfoil sample points were obtained using uniform design theory for the response surface training of Kriging model. Consequently the corresponding parameters of the airfoil were identified for optimal robust design with genetic algorithm. The influence of geometry parameters perturbation on the aerodynamic performance was discussed by applying interval analysis method. Compared with the traditional genetic algorithm, the optimization process presented has advantage in terms of time consumption.