A blading design method for both axial and centrifugal compressor blades was discussed by using arbitrary camber lines.This method was based on through flow calculation.Three dimensional blades consistent with the result of through flow calculation can be obtained by modifying the distribution of velocity circulation.Meanwhile

it can control main blade/splitter blading and the shape of trailing edge of the airfoil.It has been applied to the design of compressor blades of some micro-engines

and fairly ideal airfoils are obtained.Also

this method can be used for optimization of compressor blades.