A gas turbine engine airfoil (40,90) comprising: an airfoil tip (46, 100); an airfoil root (44, 102) opposite the airfoil tip in a spanwise direction; a leading edge (58, 106); a trailing edge (60, 108) spaced from the leading edge in a chordwise direction; first and second airfoil halves (64, 66, 94) extending between the airfoil tip and the airfoil root, the first airfoil half (66, 94) defines a suction side of the gas turbine engine airfoil, the second airfoil half defines a pressure side of the gas turbine engine airfoil and the first airfoil half is opposed from the second airfoil half in a thickness direction; and first, second and third locally-thickened regions (96(a), 96(b), 96(c)) formed in the first airfoil half, the first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in the thickness direction substantially perpendicular to the spanwise direction, and the cross-section plane extends through a middle portion of the gas turbine engine airfoil centered between leading edge and trailing edge; characterized in that the third locally-thickened region (96(c)) has a crescent-shaped geometry; and further characterized in that, starting from the airfoil root and moving toward the airfoil tip, a chord-to-chord maximum global thickness of the first airfoil initially moves toward the leading edge when transitioning from the first locally-thickened region (96(a)) to the second locally-thickened region (96(b)), recedes toward the trailing edge when transitioning from the second locally-thickened region (96(b)) toward the third locally-thickened region (96(c)), again moves toward the leading edge within the third locally-thickened region (96(c)), and again recedes toward the trailing edge before reaching the airfoil tip. an airfoil tip (46, 100); an airfoil root (44, 102) opposite the airfoil tip in a spanwise direction; a leading edge (58, 106); a trailing edge (60, 108) spaced from the leading edge in a chordwise direction; first and second airfoil halves (64, 66, 94) extending between the airfoil tip and the airfoil root, the first airfoil half (66, 94) defines a suction side of the gas turbine engine airfoil, the second airfoil half defines a pressure side of the gas turbine engine airfoil and the first airfoil half is opposed from the second airfoil half in a thickness direction; and first, second and third locally-thickened regions (96(a), 96(b), 96(c)) formed in the first airfoil half, the first airfoil half has a first multimodal thickness distribution, as taken in a cross-section plane extending in the spanwise direction and in the thickness direction substantially perpendicular to the spanwise direction, and the cross-section plane extends through a middle portion of the gas turbine engine airfoil centered between leading edge and trailing edge; characterized in that the third locally-thickened region (96(c)) has a crescent-shaped geometry; and further characterized in that, starting from the airfoil root and moving toward the airfoil tip, a chord-to-chord maximum global thickness of the first airfoil initially moves toward the leading edge when transitioning from the first locally-thickened region (96(a)) to the second locally-thickened region (96(b)), recedes toward the trailing edge when transitioning from the second locally-thickened region (96(b)) toward the third locally-thickened region (96(c)), again moves toward the leading edge within the third locally-thickened region (96(c)), and again recedes toward the trailing edge before reaching the airfoil tip.