Gas turbine engine airfoil

An airfoil for a turbine engine comprising:

• an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip, wherein the airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position, wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span, wherein the airfoil has a relationship between a leading edge dihedral and a span position, the leading edge dihedral negative from the 0% span position to the 100% span position, wherein a positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning,
• wherein the airfoil has a leading edge sweep angle curve corresponding to a relationship between a leading edge sweep angle and a span position, wherein a leading edge sweep angle at the 100% span position is less negative than a forward-most leading edge sweep angle along the curve, and wherein the curve has a decreasing leading edge sweep angle rate in a range of a 80-100% span position, and wherein the airfoil is a fan blade for the turbine engine.