Multi-objective integrated optimization of airfoil based on surrogate model

To reduce the computation burden of airfoil optimization with computational fluid dynamics method and numerical optimization technology, a multi-objective optimization approach for the airfoil was proposed. The airfoil geometry was formulated by linear perturbation method with shape functions, then, by solving N-S formulation the aerodynamic performance was obtained. Pareto Multi-objective genetic algorithm was employed in the optimization, and surrogate model was adopted to reduce computational cost. Due to optimization integration, automation of entire optimization procedure was achieved, which improved the design efficiency. The results of case studies demonstrate that this approach has reduced computation burden and shortened the design circle, which is also proved to be practicable in engineering.