a turbomachine component includes a compressor stator vane having an airfoil core shape . the airfoil core shape includes a nominal profile substantially in accordance with cartesian coordinate values of x , y , and z set forth in table 1 , and wherein x and y are distances in inches which , when connected by smooth continuing arcs , define airfoil profile sections at each distance z in inches . the profile sections at the z distances are joined smoothly with one another to form a complete airfoil core shape .