Inflatable Heat Shields (IHS) represent a breakthrough solution that supports the realization of innovative re-entry space missions by significantly increasing payload capability and enhancing space systems' recovery potential. To make this solution operational, several key technologies must be matured to an appropriate level. Within the scope of the EFESTO-2 project, structural and aerodynamic ground tests have been planned to advance our understanding of this unique inflatable aerodynamic decelerator system. To achieve this objective, a numerical study is conducted to simulate the maximum expected deformation level of the heat shield during re-entry. Subsequently, both nondeformed and deformed shapes of the heat shield are tested in the H2K and TMK wind tunnels. Following this, posttest numerical analysis will be conducted. This paper presents the efforts and achievements pertaining to the aerodynamic investigation of aeroshapes in the hypersonic wind tunnel H2K and the supersonic wind tunnel TMK. It encompasses aspects such as the specification of wind tunnel models, test conditions, measurement techniques, and the evaluation of test results.