Abstract: By the use of implicit flux-vector-splitting method, three-dimensional dimensionless conservative parabolic navier-stokes equation is solved in general curved coordinates system. The code developed can be used to solve the three-dimensional flow field with comparatively complex boundary such as the flow field that subsonic, transonic and supersonic flows appear in it, the flow field that internal and external flows exist together and their mixing wake flow with multi-blocks. An axisymmetric sub-tran-supersonic internal flow field solution of a nozzle is given here including computational grid, flow vector profile, pressure, temperature and Mach number contour line distribution. An inner and outer flow field solution of a nozzle and its mixing wake flow is also presented inside being compose of computational grid, flow vector profile, dimensionless pressure, density and temperature contour line distribution.