The purpose of this paper is to analyze the aero-elasticity characteristics of gas turbine blade on various ambient temperatures. Gas turbine blade has the specified displacement due to the disk vibration and shock on the blade surface. Disk vibration make the mode shape for symmetrical geometry like circular plate (on every nodal diameters). In addition, shock magnitude and pattern of blade surface decide the blade fluttering. The industrial turbine blade is operated on the constant design point. Actually, the induced mass flow rate is changed by the ambient temperature. Consequently, Aero-damping value is shifted by the difference of ambient temperature.