Abstract: Provided is an aerodynamic profile for use in gas turbine airfoil and a turbine blade comprising such profiles. The profiles counteract a reduction in area between adjacent airfoils due to an increase in coating thickness. A plurality of radial sections forms both coated and uncoated nominal profiles of the airfoils. The sections are located within a tolerance measured 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. The R values are measured perpendicular to a plane normal to the airfoil stacking line with R values of zero at a lowermost radial section and increasing in the radial direction. The X and Y values are measured perpendicular to the airfoil stacking line.