The internal 3-D viscous flow fields of the transonic axial-flow compressors were numerically analyzed using a time-marching finite difference method.This calculation method was developed by the LU-SGS(lower-upper symmetric Gauss-Seidel) implicit scheme and NND(non-oscillatory

containing no free parameters and dissipative) scheme with Steger-Warming flux vectors splitting technique

and the centered difference scheme was used for the viscous portion.The mixing plane model was employed to simulate the internal 3-D viscous flow fields of multistage axial-flow compressors

so the overall performance for NASA rotor 37

NASA rotor 67 and one stage compressor was obtained and the internal flow fluids were analyzed in detail.As compared with experimental data

the good agreements are found

indicating the model and method are feasible and reliable.