Abstract: In order to conduct the drag reduction optimization design of install parameters of nacelle, multi-zone FFD technique is established based on NURBS (Non-Uniform Rational B-Spline) basis function in this paper. The composite frames are founded through choosing the boundary condition of FFD shape and lattice reasonably. Then, it can realize the FFD parameterized design of the multi-control frames for complex shape in different zones. This multi-control frame FFD technique is used to conduct drag reduction design of the install position of certain airliner nacelle. The aerodynamic optimization design system is established by combining FFD technique, random inertia weight PSO arithmetic and Kriging surrogate model. It process the aerodynamic optimization design by taking horizontal install position and horizontal torsion angle of certain airliner nacelle as design variables, and the results show that the optimized nacelle has lower drag and better aerodynamic characteristic in certain attack angle. Therefore, the optimization design system based on multi-zone FFD technique established in this paper is reasonable and practical.