Optimization of the last stage guide vane of the axial compressor is carried out in order to reduce the outflow swirl at compressor exit. Turning angle and total pressure losses are considered as optimization criteria. Parametric model was designed for 2D airfoil, where coordinates of points on the profile are taken as variables. CFD computations are made in Ansys CFX and optimization is carried out in IOSO. As a result exit flow swirl decreased with the same pressure losses and also possible solution for much higher outflow angle with higher losses is proposed. CFD computations of the whole compressor were done for initial and optimized blades.