Prediction of Gross Parameters during Enclosed Incineration of Energetic Materials

Document Type



A computational technique that can be used to predict the transient air temperature and pressure response when rocket propellant or other energetic material is incinerated in an enclosed space is described. An energy balance is used with details of the heat transfer to the wall of the enclosure. This approach has been applied to estimate transient pressure and temperature response for two series of incinerations at the Nevada Test Site. These tests were performed to dispose of outmoded solid rocket propellant, and they were performed in a sealed-off underground chamber. Results of the model correlate quite well with the experimental data considering the very complicated phenomena that are taking place.


Hazardous wastes – Incineration; Nevada – Nevada Test Site; Pressure; Rockets (Aeronautics) – Fuel; Solid propellants; Temperature


Heat Transfer, Combustion | Mechanical Engineering


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