Compressor rotor blade airfoils

A turbomachine comprising:

• a compressor section;
• a turbine section downstream from the compressor section;
• a combustion section downstream from the compressor section and upstream from the turbine section;
• and
• two or more rotor blades disposed within the compressor section of the turbomachine, each rotor blade of the two or more rotor blades comprising:
• an airfoil having an airfoil shape, the airfoil shape having a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I, the Cartesian coordinate values of X, Y, and Z being defined relative to a point data origin at a base of the airfoil, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values from 0% to 100% convertible to dimensional distances expressed in a unit of distance by multiplying the Cartesian coordinate values of X, Y and Z by a height of the airfoil in the unit of distance;
• and wherein X and Y values, when connected by smooth continuing arcs, define airfoil profile sections at each Z value, the airfoil profile sections at Z values being joined smoothly with one another to form a complete airfoil shape.