Abstract: An aerodynamic optimization design method for wing/nacelle integration based on genetic algorithm optimization/Navier-Stokes analysis (GA/NS) is presented in this paper. A series of solutions, including the modularization of design parameters, the local optimization with full configuration analysis, and the constraints on supercritical pressure distribution, etc., are proposed to improve the engineering applicability of the aerodynamic optimization. Through the use of a verified "design grid", parallel computing and advanced numerical methods, the turnover time of genetic algorithm optimization/Navier-Stokes analysis design is made acceptable for engineering application. Single-point and dual-point optimizations for the wing/engine nacelle integration of a wing-mounted twin-jet are presented. The comparisons of the design results demonstrate the effectiveness and the engineering applicability of the method. Pressure distributions of the single-point optimization result are shock-free. Its drag coefficient increases abruptly before the desired drag divergence Mach number. Pressure distribution of the dual-point optimization result contains a weak shock. The drag coefficient varies smoothly with the Mach number. The dual-point optimization design is more robust than the single point design and more applicable in engineering.

Key words: optimization design, genetic algorithm, constraint on pressure distribution, wing/nacelle integration, dual-point optimization