Multi-objective aerodynamic optimization of supercritical wing with substantial pressure constraints
Tong Zhao, Yufei Zhang, Haixin Chen · 53rd AIAA Aerospace Sciences Meeting · 2015
A multi-objective aerodynamic optimization of supercritical wing of a wide-body aircraft based on genetic algorithm and CST parameterization method is presented in this paper. Favorable pressure distributions of a “supercritical type” wing are considered as a lot of constraints in the optimization process. Geometry constraints and aerodynamic constraints are also employed. A full potential solver is adopted as a low fidelity aerodynamic analysis tool for preliminary optimization. A Reynolds Averaged NavierStokes solver is used as high fidelity tool for detailed optimization, and design validation. With more than 150 constraints, the optimized design has a typical supercritical pressure distribution. The CFD results also show that the design has a superior aerodynamic performance.