This study investigates the detumbling capabilities of SPICEsat following an initial angular disturbance imparted by the deployer. SPICEsat, which stands for Sloshing Platform for In Orbit Controller Experimentation, is a 6U CubeSat developed by Rutgers University to investigate the effects of fuel sloshing on spacecraft stability and control. Top level, this research's objective is to confirm SPICEsat's ability to reduce angular momentum, thereby achieving a stabilized post-deployment attitude. This is referred to as detumbling, or the process of reducing a satellite's rotational rates following deployment. The system-level focus centers on assessing the control authority of the Blue Canyon Technologies (BCT) XACT-50 unit's torque rods to counteract the angular momentum arising from both the satellite and its internal slosh fluid dynamics. A closed-loop simulation, developed in OpenFOAM, serves as the primary tool for low-level verification. The satellite is modeled as a rigid body subjected to a uniform magnetic field, with simulations conducted under conditions reflecting the maximum and minimum magnetic field strengths encountered in Low Earth Orbit (LEO). Initial conditions incorporate predefined angular momentum for the satellite body and specific fluid dynamics parameters. The control system actuates the satellite attitude through torque rods, with applied torques calculated based on magnetic field interactions. To underscore the necessity of closed-loop control, an open-loop simulation is initially presented, wherein a predetermined torque impulse is applied to counteract the initial angular momentum. The inherent limitations of this approach highlight the advantages of closed-loop control mechanisms. Subsequent simulations demonstrate closed-loop controllers utilizing two distinct methodologies: (1) a state vector-based approach assuming a uniform magnetic field and (2) a B-Dot control strategy accounting for temporal variations in the magnetic field. The outcomes validate SPICEsat's detumbling proficiency and confirm the BCT XACT-50 torque rods' efficacy in maintaining satellite attitude stability in LEO environments.