Design optimization of a transonic compressor rotor (NASA rotor 37) using the response surface method (RSM) and three-dimensional Navier-Stokes analysis has been carried out in this work. The Baldwin-Lomax turbulence model was used in the ow analysis. Three design variables were selected to optimize the stacking line of the blade. Data points for response evaluations were selected by D-optimal design, and a linear programming method was used to optimize the response surface. As a main result of the optimization, adiabatic ef ciency was successfully improved. It was found that the optimization process provides reliable design of a turbomachinery blade with reasonable computing time.