Abstract: A new numerical method for predicting the profile loss of turbine blades in subsonic and supersonic flows is presented.The profile loss consists of two parts:friction loss in the boundary layer on pressure and suction surfaces and mixing loss due to the interaction between wake and mainstream.A time-marching finite-volume Euler solver is used for mainstream calculation while a finite-difference computation for the boundary layer.A local C-grad correction is used in mainstream calculation and a full implicit difference scheme is applied to the boundary layer calculation.On the basis of mass,momentum and energy consrvation laws,the mixing loss is obtained between cascade exit and the far uniform downstream and compared with several experimental data.It is shown that this numerical method can make quite precise prediction of turbine blade profile loss.