Wing Design Optimization and Stall Analysis with Co-flow Jet Active Control

Coupled with Co-flow Jet (CFJ) technology, the Non-Dominated Sorting Genetic Algorithm II (NSGA-II) was utilized for the multi-objective combination optimization of an Optimized Co-flow Jet (OCFJ) wing, based on National Advisory Committee for Aeronautics (NACA) 6421. A high-precision numerical simulation using the Delayed Detached Eddy Simulation (DDES) model was performed on the optimized wing to investigate the three-dimensional flow separation characteristics after static stall. The stall improvement was investigated by adjusting the momentum coefficient of the injection. The results show that the optimized wing exhibits significant improvements in aerodynamic performance and corrected aerodynamic efficiency. At an angle of attack of 10◦, the average lift increased by 16.25% and the drag decreased by 27.23% compared to the CFJ6421 wing, while effectively addressing the problem of low modified aerodynamic efficiency of the CFJ wing at lower angles of attack. By utilizing higher momentum and improving the boundary layer control capability, flow separation is effectively suppressed, thus achieving the goal of stall recovery of the CFJ wing.