I am learning my way with Simulation as I am new to this world. I am trying to figure out how I can conduct a transient thermal analysis that will show the heat conducting through the layers of a rocket nozzle as a function of time. Here is what I do know upfront. I know the stagnation (recovery) temperature at several locations through the nozzle along with the material properties. I also know the heat transfer coefficients for each of the given areas where the insulation is coming in contact with the combustion stream. Is this something I could run by applying my initial temperature condition and by some way using the heat flux under the thermal load options? Again, new to this world and appologize for my lack of understading.