Turbine engine airfoil

A turbine engine, comprising:

• a compressor section, a combustion section, and a turbine section in serial flow arrangement, and
• an airfoil comprising:
• an outer wall having an exterior surface and bounding an interior, the outer wall defining a pressure side and a suction side and extending between a leading edge and a trailing edge to define a mean camber line extending between the leading edge and the trailing edge;
• a first thickness (T1) defined between the pressure side and the suction side in a first direction perpendicular to the mean camber line of the airfoil at a first location (L1) along the mean camber line, wherein the first thickness T1 is between 0.147 cm and 0.269 cm (0.147 cm≤T1 ≤0.269 cm);
• a second thickness (T2) defined between the pressure side and the suction side in a second direction perpendicular to the mean camber line at a second location (L2) along the mean camber line, wherein the second thickness T2 between 0.353 cm and 0.693 cm (0.353 cm≤T2≤0.693 cm);
• wherein the second location L2 is positioned farther from the trailing edge than the first location L1;
• and
• a distance (dT) defined along the mean camber line between the first location L1 and the second location L2, wherein the distance dT is between 0.559 cm and 1.313 cm (0.559 cm≤dT≤1.313 cm);
• wherein the first thickness T1 and the distance dT define a first ratio (R1) as R1=dT/T1, wherein the first ratio R1 is between 2.5 and 6.5 (2.5≤R1≤6.5);
• wherein the first thickness T1, the second thickness T2, and the first ratio R1 are related to each other as
• (
• T
• 2
• T
• 1
• -
• 1
• )
• /
• R
• 1
• to define a thickness parameter (τ);
• wherein the thickness parameter τ is between 0.275 and 0.45 (0.275≤τ≤0.45).