On the basis of statistical data and analysis of axial flow compressors

the ratio of trailing edge momentum thickness to chord length θ/c and trailing edge form factor H are determined by the use of equivalent diffusion factor D eq

and then the profile loss of the blade is obtained after appropriate corrections.Finally

the total loss distribution along the blade span of the axial flow compressor is estimated according to an improved end wall loss model and a shock loss model.An extensive comparison of the estimated loss data with the original design and test data shows that the loss model presented here is feasible for normal blade profile

double circular arc blade profile and multi circular arc blade profile of axial flow compressor

and the accuracy of the estimation is improved greatly.As a part of S 2 flow surface program

a computer subprogram has been worked out based on this approach.It gives satisfactory results of the flow field computation and is also very simple and practical.The subprogram can meet all requirements of aerodynamic design and analysis for an advanced axial flow compressor.