This paper describes the SPONGE experiment (Sounding rocket Propellant OrieNtation microGravity Experiment) developed at CISAS in collaboration with Thales Alenia Space Italy. The aim of this experiment is to provide the data for the validation of the CFD code created to study and design propellant management devices. SpongeCompressibleFoam is a code based on the OpenFOAM Platform, written at CISAS to simulate propellant management devices. The latter are passive static metal structures used in rocket tanks to control propellant behavior; they work using surface tension to ensure gas-free liquid delivery to the tank outlet. SPONGE flew on board the REXUS 9 ESA/SSC/DLR sounding rocket in February 2011, it is based on two counter rotating plates: (i) the experimental plate, on which the control equipment and a polycarbonate tank containing the sponge test-sample are placed and (ii) the balancing plate, rotating in the opposite direction with respect to the experimental plate and ensuring no momentum transfer to the rocket. The system rotates at four different angular velocities, allowing the study of the sponge and its retention capability under different centrifugal forces. The design and results are presented.