The applicability of numerical procedure has been contemplated for the problem of ignition transient in the solid rocket motor. A numerical simulation is completed to analyze the ignition transient both head-end and aft-end ignition system. Time-dependent compressible SIMPLER algorithm for gas phase governing equations and finite volume method (FVM) for radiative transfer equation are employed, respectively. Two dimensional conduction equation for propellant grain is combined as well. While the standard k-ε model with wall function is used for turbulence, the eddy break-up (EBU) model is used for gas phase reaction rate.
A reasonably good agreement with the experiment is obtained in predicting a variation of head-end pressure for the case of head-end ignition. Based on this comparison, a detailed development of unsteady turbulent combustion flow field is obtained and is helpful for understanding the physical phenomena involved. Especially, the radiation is found to play a significant role in igniting the solid propellant by promoting the heat feedback to propellant surface. However, without radiation, no successful ignition and flame spreading cannot be obtained for the conditions given in this study.