Transonic Nacelle Aerodynamic Optimization Based on Hybrid Genetic Algorithm

摘要

Aerodynamic optimization study of a transonic nacelle is presented in this paper. The method of "Class Shape Transformation" is developed to parameterize the non-axis symmetrical nacelle geometry. Based on a hybrid genetic algorithm, which combines a genetic algorithm with the Kriging response surface model, the efficiency of the optimization process is well improved. Steady Reynolds-Averaged Navier-Stokes (RANS) equations with SST turbulence model are used for aerodynamic analysis. Optimized results of axis-symmetry and three-dimensional non-axis symmetrical nacelles are discussed and compared with the initial designs. With appropriate constraints, the optimized nacelle can obtain a better aerodynamic performance without internal volume penalty.