In this paper, a method for the flutter evaluation for gas turbine axial compressor blade was studied. For predicting the flutter phenomena, determination of the aerodynamic damping is important task. Recently, aerodynamic damping predicted by the energy method in frequency domain. Flutter calculations consist of unsteady aerodynamic and modal analysis. ANSYS CFX used to predict unsteady fluid flow in transonic blade and work per cycle of blade for aerodynamic damping. ANSYS Mechanical used to mode analysis of bladed disk and mode shape extraction for blade deformation. Through the flutter calculation, aerodynamic damping distributions with various nodal diameter was derived also, compressor performance map which is the considering flutter boundary was presented.