A software is designed to calculate steady subsonic and transonic blade flows.It can analyse the features of the flow field according to the boundary conditions and automatically choose the numerical method which is suitable to obtain the accurate results and save calculation time.When the coordinates on blade surface at inlet and outlet are given

user can determine Mach number or pressure distribution on blade surface

Mach number or pressure contours in all of the flow field.Two kinds of the numerical methods are programmed in this software:Streamline curvature method and Time-matching method.The former directly starts from steady Euler equations

since the multi-value problem in transonic flows was solved by the author

the streamline curvature has been successfully used to compute transonic flow

especially it gets rapid covergence when the flow is subsonic at outlet.The later method starts from unsteady Euler equations but with constant total enthapy.The steady flow is calculated as the asymptotic limit after a sufficient long time of solution of the unsteady equations.This method with appropriate scheme and shock capturing technique is accurate to compute transonic flow with shock

but in the case of subsonic at outlet

the streamline curvature method can reduce the calculation time approximately 60%.Three numerical examples are given in this paper.Both the calculation methods give comparable results and the results agree well with the measurements.