CFD Modeling of a Cryogenic Methane Drain Test with and without Induced Sloshing

Current planned NASA missions to the Moon and Mars involve the transfer of cryogenic propellants in orbit. These activities require large amounts of cryogenic propellant and the ability to transfer these fluids from one tank to another in an efficient manner. Predicting the pressurant required for the supply tank pressurization during the initial pressurization and expulsion process will be important to understand priori to reduce propellant margin.