Abstract: A flux-splitting implicit finite volume method under an arbitary non-orthogonally curvilinear grid system is developed for the calculation of the axisymmetrical flow. The expression for the calculation of the two-dimensional and axisymmetric flow is unified. Decomposition and classification of the viscous flux are performed,so the contribution of all terms to the implicit increment,including the cross-derivative terms,is taken into account in this method The calculation of the flow with a centered jet shows that the method is superior to the MacCormack explicit scheme in both accuracy and convergence rate The computation of the strong interaction flow with transverse injection reveals primarily the producing mechanism of the indirectly propulsive force of the attitude control nozzle According to this,the requirement for the rated propulsive force of the nozzle can be degraded in desgin.

Key words: finite volume method, flux vector splitting, jet flow, supersonic flow interference