Gas turbine engine airfoil

1. An airfoil for a turbine engine comprising:

an airfoil having pressure and suction sides and 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 0° to 10° in a range of 10-20% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span.

2. The airfoil according to claim 1 , wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position.

3. The airfoil according to claim 2 , wherein the trailing edge sweep angle is about 15°.

4. The airfoil according to claim 1 , wherein the trailing edge sweep angle is positive from 0%-95% span.

5. The airfoil according to claim 4 , wherein the trailing edge sweep angle transitions from less positive to more positive at greater than an 80% span position.

6. The airfoil according to claim 4 , wherein a positive-most trailing edge sweep angle is at a greater than 50% span position.

7. The airfoil according to claim 1 , wherein a trailing edge sweep angle at the 0% span position and a trailing edge sweep angle at the 100% span position are about the same.

8. The airfoil according to claim 7 , wherein a positive-most trailing edge sweep angle is at about a 70% span position.

9. The airfoil according to claim 1 , wherein a trailing edge sweep angle is within 5° along a portion of the curve from the 0% span position to a 60% span position.

10. The airfoil according to claim 9 , wherein a positive-most trailing edge sweep angle lies along the portion.

11. The airfoil according to claim 9 , wherein a trailing edge sweep angle at the 0% span position and a trailing edge sweep angle at the 100% span position have a differential in a range of 40° to 50°.

12. The airfoil according to claim 1 , wherein a positive-most trailing edge sweep angle is within the range of 10° to 20° in the range of 40-70% span position.

13. The airfoil according to claim 1 , wherein the airfoil has a 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.

14. The airfoil according to claim 13 , wherein the curve has a portion extending span-wise toward the tip and from the forward-most leading edge sweep angle, the portion has a decreasing leading edge sweep angle that crosses a zero sweep angle in the range of a 30-40% span position.

15. The airfoil according to claim 14 , wherein the forward-most leading edge sweep angle is in a range of −10° to −15°.

16. The airfoil according to claim 15 , wherein the forward-most leading edge sweep angle is about −10°.

17. The airfoil according to claim 15 , wherein a rearward-most leading edge sweep angle is in a range of 15° to 30°.

18. The airfoil according to claim 17 , wherein the rearward-most leading edge sweep angle is in a range of 75-85% span position.

19. The airfoil according to claim 14 , wherein a leading edge sweep angle at the 0% span position and a leading edge sweep angle at the 100% span position are within 5° of one another.

20. The airfoil according to claim 19 , wherein the leading edge sweep angle at the 0% span position and a leading edge sweep angle at the 100% span position are positive.

21. The airfoil according to claim 14 , wherein a leading edge sweep angle at the 0% span position is negative, and a leading edge sweep angle at the 100% span position is positive.

22. The airfoil according to claim 21 , wherein the leading edge sweep angle at the 0% span position and the leading edge sweep angle at the 100% span position are within 10° of one another.

23. The airfoil according to claim 2 , wherein a leading edge sweep angle at the 0% span position is positive, and a leading edge sweep angle at the 100% span position is negative.

24. The airfoil according to claim 1 , wherein the airfoil is a fan blade for a gas turbine engine.

25. A gas turbine engine comprising:

a combustor section arranged between a compressor section and a turbine section;

a fan section has an array of fan blades and a low fan pressure ratio of less than 1.55; and

wherein the fan blades include an airfoil having pressure and suction sides, the airfoil extends 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 0° to 10° in a range of 10-20% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span.

26. The gas turbine engine according to claim 25 , wherein the array includes twenty-six or fewer fan blades; and

a geared architecture couples the fan section to the turbine section or the compressor section.

27. The gas turbine engine according to claim 26 , wherein the trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position.

28. The gas turbine engine according to claim 26 , wherein the low fan pressure ratio is less than 1.52.

29. The gas turbine engine according to claim 28 , wherein the low fan pressure ratio is less than 1.50.

30. The gas turbine engine according to claim 29 , wherein the low fan pressure ratio is less than 1.48.