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An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span positi

An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil is a fan blade for a gas turbine engine. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning.

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1. 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 relationship between a leading edge dihedral and a s

1. 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 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 is a fan blade for a gas turbine engine; andwherein the airfoil has a relationship between a trailing edge dihedral and a span position, the trailing edge dihedral positive 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. 2. The airfoil according to claim 1, wherein the leading edge dihedral at the 0% span position is in the range of −3° to −12°. 3. The airfoil according to claim 2, wherein the leading edge dihedral at the 0% span position is about −4°. 4. The airfoil according to claim 2, wherein the leading edge dihedral at the 0% span position is about −10°. 5. The airfoil according to claim 2, wherein the leading edge dihedral extends from the 0% span position to a 20% span position having a leading edge dihedral in a range of −2° to −6°. 6. The airfoil according to claim 5, wherein the leading edge dihedral includes a first point at a 75% span position and extends generally linearly from the first point to a second point at the 85% span position. 7. The airfoil according to claim 6, wherein the first point is in a range of −8° to −10° dihedral. 8. The airfoil according to claim 6, wherein the second point is in a range of −3° to −6° dihedral. 9. The airfoil according to claim 2, wherein a maximum negative dihedral is in a range of 95-100% span position. 10. The airfoil according to claim 9, wherein a least negative dihedral is in a range of 5-15% span position. 11. The airfoil according to claim 2, wherein a maximum negative dihedral is in a range of 65-75% span position. 12. The airfoil according to claim 11, wherein a least negative dihedral is in a range of 0-10% span position. 13. The airfoil according to claim 2, wherein a maximum negative dihedral is in a range of 50-60% span position. 14. The airfoil according to claim 13, wherein the relationship provides a generally C-shaped curve from the 0% span position to a 50% span position and then a 90% span position. 15. The airfoil according to claim 14, wherein a trailing edge dihedral at the 0% span position is in a range of 20° to 25°. 16. The airfoil according to claim 15, wherein a trailing edge dihedral at about the 50% span position is in a range of 2° to 6°. 17. The airfoil according to claim 15, wherein a trailing edge dihedral at the 90% span position is in a range of 16° to 22°. 18. The airfoil according to claim 15, wherein from a 65% span position to a 75% span position the trailing edge dihedral increases about 5°. 19. The airfoil according to claim 16, wherein a positive-most trailing edge dihedral in a 80%-100% span position is within 5° of the trailing edge dihedral in the 0% span position. 20. The airfoil according to claim 15, wherein a least positive trailing edge dihedral is in a 40%-55% span position. 21. The airfoil according to claim 14, wherein the airfoil is a fan blade for a gas turbine engine.