Applying the ball-spine algorithm to the design of blunt leading edge airfoils for axial flow compressors

An inverse design algorithm, called the ball-spine (BS) algorithm, is developed for the design of axial flow compressor blades. This algorithm has been previously applied to the design of 2D sharp leading edge airfoils. In the present study, the BS algorithm is extended to the design of blunt leading edge compressor blade sections. The algorithm receives a target pressure loading and an initial guess for its geometry. Through the design procedure, the geometry is evolved until the target pressure is achieved. The accuracy of the method is assessed against two airfoils, namely, NACA65-410 (with the initial guess for geometry as a flat-plate-airfoil) and NACA65-610 (with the initial guess for geometry as NACA65-410). The method is shown to be efficient and accurate, and can capture the target geometry in approximately 50 evolutions. As an application, a new airfoil with 5% more lift than NACA65-610 is designed, for which NACA65-610 geometry is used as the initial guess.