GAS TURBINE ENGINE AIRFOIL

An airfoil (64) for a turbine engine (10) includes pressure and suction sides (72, 74) that extend in a radial direction (R) from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip (66). The airfoil (64) has a relationship between a total chord length (L) and a span position corresponding to a curve having an increasing total chord length (L) from the 0% span position to a first peak, the first peak occurs in the range of 45-65% span position, wherein the total chord length at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm), the first peak is provided by a critical point in a range of 50-60% span position, a slope from the critical point to an inflection point is substantially zero, and the inflection point is in a range of 70-80% span position.