Modeling of Radiation Heat Transfer in Liquid Rocket Engines

Concluding Remarks• For a LH2/LO2 engine it is shown that theradiation has a small effect on the walltemperature of the diverging section of thenozzle• the radiation results in a substantial increase inthe wall temperature of the thrust chamber andconverging section of the nozzle, such that thelocal peak temperature is the same order ofmagnitude as the throat temperature