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Sloshing of cryogenic liquid propellants in launch vehicle tanks creates unwanted thermodynamic side-effects such as pressure changes in the tank. The goal of this PhD research was to develop a practical engineering model which is able to describe the influence of the sloshing of a cryogenic liquid on the heat and mass transfer and the associated temperature and pressure. The pressure changes caused by sloshing were investigated experimentally and numerically. Using the experimental and numerical results, a one dimensional (1D) engineering model was developed which is able to describe the experimental results.