A computer code to calculate two-dimensional or axisymmetric compressible internal flows is developed based on u-v-p-T formulation and an approximate factorization(AF) technique. Computations are carried out for a two dimensional shock tube problem, an incompressible(M=0.05) laminar driven cavity problem, a JPL nozzle, a two dimensional planar(area ratio:AR=18) and an axisymmetric(AR=324) convergent-divergent nozzle flows. The results are compared with those of other numerical method based on conservative variables. The comparison shows that the present code works properly and is effective for the low subsonic Mach number flows.