An airfoil for a gas turbine engine , comprising: a substrate portion extending from an airfoil leading edge to an airfoil trailing edge portion , the substrate portion comprising: a substrate body; an airfoil leading edge disposed at a first end of the substrate body; and an airfoil trailing edge portion disposed at a second end of the substrate body opposite the first end, the airfoil trailing edge portion including: a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil; and a trailing edge defined as a selected shape extending from a pressure side of the airfoil to a suction side of the airfoil; and a coating portion comprising a coating applied over at least a portion of the substrate portion , the coating portion comprising: a body portion having a substantially constant coating thickness ; and a taper portion disposed between the body portion and the trailing edge ; characterized in that , the taper portion extends to a coating edge disposed upstream of the trailing edge , the coating edge located forward of a maximum thickness location of the flared portion . a substrate portion extending from an airfoil leading edge to an airfoil trailing edge portion , the substrate portion comprising: a substrate body; an airfoil leading edge disposed at a first end of the substrate body; and an airfoil trailing edge portion disposed at a second end of the substrate body opposite the first end, the airfoil trailing edge portion including: a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil; and a trailing edge defined as a selected shape extending from a pressure side of the airfoil to a suction side of the airfoil; and a substrate body; an airfoil leading edge disposed at a first end of the substrate body; and an airfoil trailing edge portion disposed at a second end of the substrate body opposite the first end, the airfoil trailing edge portion including: a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil; and a trailing edge defined as a selected shape extending from a pressure side of the airfoil to a suction side of the airfoil; and a flared portion wherein a substrate portion thickness increases along a camber line of the airfoil; and a trailing edge defined as a selected shape extending from a pressure side of the airfoil to a suction side of the airfoil; and a coating portion comprising a coating applied over at least a portion of the substrate portion , the coating portion comprising: a body portion having a substantially constant coating thickness ; and a taper portion disposed between the body portion and the trailing edge ; characterized in that , the taper portion extends to a coating edge disposed upstream of the trailing edge , the coating edge located forward of a maximum thickness location of the flared portion . a body portion having a substantially constant coating thickness ; and a taper portion disposed between the body portion and the trailing edge ; characterized in that , the taper portion extends to a coating edge disposed upstream of the trailing edge , the coating edge located forward of a maximum thickness location of the flared portion . <EOS>