Numerical validation and analysis of supersonic retropropulsion test cases

Supersonic retro-propulsion (SRP) represents a promising technique to slow down a space vehicle during the descent phase of human Mars exploration class missions. Aerodynamics appears since the 60s among the fields of interest concerning the application of SRP, and it is still an important topic of research and development. The aim of this paper is twofold. On the one hand, we use CFD to understand the complex flowfields arising from the application of supersonic retro-propulsion using different nozzle configurations and different jet/freestream conditions. On the other hand, we compare numerical results with experimental data and other CFD results in a validation and verification exercise. Such activity is needed to define best practice guidelines and to build confidence in the reliability of numerical simulations that replicate SRP. It is an important starting point for future design-oriented applications that should include realistic high-temperature, reacting jet configurations in Mars-relevant conditions, which are unlikely to be tested in ground-based facilities