Aerodynamic Analysis of Supersonic Parachutes during Atmospheric Entry Descent Phase using Computational Fluid Dynamics (CFD)

Since the beginning of space exploration, atmospheric reentry has presented a complex and crucial challenge for several reasons. The ability to decelerate properly and safely, the precision of reaching the intended landing site and the integrity of the payload are some of the main role of EDL systems. In this context, the most reliable and widely used deceleration method involves the use of supersonic parachutes. These systems must ensure effective operation both in supersonic and subsonic regimes. The aim of this thesis is to examine the aerodynamic performance of a Disk-Gap-Band parachute in terms of aerodynamic drag and stability by varying some of its main features, with a focus on Mach, the distance between the capsule and the parachute, and the size of the parachute. In order to do this, the role of computational fluid dynamics (CFD) play a relevant role. For this study, the CFD software "STARCCM+" by Siemens was employed. The study started with model validation using data from previous investigations. Subsequently, the parametric study phase began, and the results will be presented and discussed in detail.