Systems and methods for modifying a pressure side on an airfoil about a trailing edge

A method for improved flow turning and lift in an axial compressor, comprising:

• starting with an airfoil as depicted in FIG. 2, wherein the airfoil comprising a leading edge, a trailing edge, a suction side defined between the leading edge and the trailing edge, and a pressure side defined between the leading edge and the trailing edge opposite the suction side;
• and
• modifying the pressure side about the trailing edge to from a concave profile about the trailing edge that varies from a profile of a remainder of the pressure side as denoted by a transition point without modifying the suction side, which modifies a thickness distribution about the trailing edge, which in turn modifies an effective camber of the airfoil to increase an effective camber of the airfoil without modifying the suction side.