Inverse problem study of isolated wing by genetic algorithm

The Genetic Algorithm (GA), coupled with the potential flow solver KTRAN, was successfully applied to redesigning the ONERA M6 wing. A 6th order B-spline curve was used to represent each section of the wing. The actual values of the (x, y) coordinates of the control nodes for the B-spline curves were designated as the design variables. The least squares difference between the actual and target pressures was used as the objective function. The NACA0012 airfoil section was taken as an initial geometry. Both pressure distributions and geometry of the redesigned wing agreed well with their target values, demonstrating the ability of this technique. (author)