Numerical simulation for failure of nozzle burn-through in solid rocket motor

A high resolution TVD (Total Variation Diminishing) MacCormack scheme was used to solve the 2-D axisymmetric N-S equation in a large solid rocket motor nozzle. The details of flow fields were examined carefully in order to find the reason of burn-through failure. The research results show that the derivative function discontinuity of nozzle profile can cause a sudden rise of temperature, which greatly enhances the burning erosion of nozzle profile and may be the direct reason of the failure. This conclusion agrees with the results of simulation tests.