This paper documents a numerical model, developed for the McGill Rocket Team based on classical chemical thermodynamics coupled with the Trebble-Bishnoi equation of state, to solve for the oxidizer tank conditions (pressure, temperature, mole flowrate and liquid/vapour equilibrium) during the operation of a hybrid rocket. This model is modular and can be coupled to fluid mechanics and combustion chamber models for a more detailed analysis of a hybrid rocket engine.
We compare major factor models and find that the Stambaugh and Yuan (2016) four-factor model is the overall winner in the time-series domain. The Hou, Xue, and Zhang (2015) q-factor model takes second place and the Fama and French (2015) five-factor model and the Barillas and Shanken (2018) six-factor model jointly take third place. But the pairwise cross-sectional R2 and the multiple model comparison tests show that the Hou, Xue, and Zhang (2015) q-factor model, the Fama and French (2015) five-factor and four-factor models, and the Barillas and Shanken (2018) six-factor model take equal first place in the horse race.