Flux vector splitting algorithms for the whole of subsonictransonic-supersonic nozzle flows

The Navier-Stokes equations were used and the algebraic model was adopted for the turbulent calculations. The computational efficiency of several different schemes were compared with each other and the direct solution by flowfield partitioning was used. The computed results of transonic flow were compared to the test and other's computed results. It has been discovered that it is necessary to deal with the subsonic, supersonic or reverse flow boundary conditions respectively at the outlet. The Mach number in the boundary layer changes very sharply along the direction perpendicular to the wall. The change of wall temperature or Re number can lead to the change of the thickness of boundary layer.