NURBS method was applied to reshape some supersonic airfoils

and two controlling parameters were used to adjust the geometric shape of supersonic airfoil’s leading edge

these methods were adopted to investigate the supersonic airfoil’s aero-dynamic performance influence effect with different leading edge geometric shape; The contrastive analysis results

which were obtained from a series of airfoil’s flow field structure with changing each controlling parameter

shown ellipse shape controlling factor not only could weaken the shock wave intensity near the leading edge region of airfoil but also could improve the flow field structure; At the same time

this paper demonstrated that the matching between some ellipse shape controlling factor and some ellipse direction controlling factor could make the responding supersonic airfoil’s aero-dynamic performance reach to the best while its chord keeping no change.