Design and numerical optimization of flatback airfoils

An aerodynamic optimization design method based on the surrogate model was used for design and numerical optimization of the flat back airfoil of wind turbine with a splitter plate at the trailing edge. The aerodynamic property of the airfoil was obtained by numerically simulating flow around flat back edge airfoils and by solving the Reynolds-averaged Navier-Stokes equation in which the SST k-Ω turbulence model coupling γ-R^~e_θ transition model was employed. In this optimization process, the sectional moment of inertia of the airfoils and the lift coefficient at high angle of attack were taken as two objectives, while the drag and moment coefficients and some other properties were taken as constraints. The results show that the lift coefficient at the angle of attack of 17° is increased by 8.53%, the maximum lift coefficient is increased by 3.13%, and the sectional moment of inertia is increased by 7.84%, while the optimized flat back airfoil meets all the constraints.