 Aerodynamic studies in the 1960s demonstrated that the "vortex lift" phenomenon could be harnessed by highly swept wing configurations to reach higher angles of attack, using leading edge vortex flow off a slender lifting surface.As the F-16 was being optimized for high combat agility, GD's designers chose a slender cropped-delta wing with a leading edge sweep of 40° and a straight trailing edge.To improve maneuverability, a variable-camber wing with a NACA 64A-204 airfoil was selected; the camber is adjusted by leading-edge and trailing edge flaperons linked to a digital flight control system (FCS) regulating the flight envelope.