A small turbojet, the SR-30, is often used in academic settings to demonstrate thrust generation. The experience and insights afforded by this type of experimentation we find invaluable, because the students appraise a turbojet, from start-up to wind down, in all its dimensions: from basic thermodynamics to creep considerations, passing through instrumentation and lubrication. Experimental uncertainties of measurements taken on this unit lead to conflict with basic thermofluids laws, and have been reported in the literature. The present work introduces a thermodynamic model whereby the thrust can be calculated for a range of speeds. The model resorts to conservation principles and efficiencies to factor in the turbine irreversibilities. Six significant variables are assigned uncertainties, and a thrust distribution is generated via a Monte-Carlo analysis. The parameters of the thrust distribution are analyzed to determine the reliability of thrust predictions. Intermediate cycle temperatures can be estimated via an approach consistent with the thermo-fluids laws.