A computer code to calculate two-dimensional or axisymmetric compressible internal flows is developed based on TVD(total variation diminishing) scheme and LU-SSOR(lower-upper symmetric successive overrelaxation) algorithm. Flows of a ramjet nozzle, the JPL nozzle, and the nozzle to accelerate working fluid to Mach number 5 are computed using the code. Computational results for these cases are compared with experimental data available. Temperature distribution along the wall in the JPL nozzle is obtained and the viscous solution is compared with the inviscid solution. It can be seen that there is big difference between these two especially in supersonic region and that turbulent flow calculation is necessary to analyze the case for nozzle flow accelerated beyond Mach number 5.
