Pampero HiFi: improvements in aerodynamic modeling of a spacecraft-oriented destructive re-entry code

Abstract This work presents the CFD module developed in the scope of the implementation of the high-fidelity branch of the spacecraft-oriented re-entry tool. First, the Riemann solver, the immersed boundary method, and the adaptive mesh refinement of are briefly detailed. The mass loss generated by the chosen immersed boundary method is investigated on a sphere and a satellite case. Then, the results of the simulation of static hypersonic wind tunnel test cases are presented. A part of a cube’s trajectory computed by the modified Newton theory (method used in spacecraft-oriented tools) is computed using the pressure loads of . The impact of the fluid modeling on the stability of the object is shown. Finally, the surface pressure distribution and the aerodynamic coefficients obtained with a body-fitted CFD reference code, the modified Newtonian theory and on a satellite case are compared. shows major improvement compared to the modified Newtonian theory.