Airfoil profile with optimized aerodynamic shape

A gas turbine blade comprising:

• an airfoil profile, said profile having a nominal and uncoated shape formed by fairing a plurality of radial sections, said sections located within an envelope of ±0.006 inches in any direction perpendicular to an airfoil stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1;
• and
• wherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line.

A turbine blade comprising:

• A coated airfoil profile, said profile having a shape formed by fairing a plurality of radial sections, said sections located within an envelope of between −0.004 and +0.020 inches in any direction perpendicular to an airfoil stacking line, said stacking line extending radially from a central axis and defined by X, Y, and R Cartesian coordinate values in inches as listed in Table 1;
• and
• wherein R is a perpendicular distance from a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction and the X and Y values are perpendicular distances from the airfoil stacking line.