This paper deals with launcher aerodynamic design activities at phase-A level. The goal is to address the preliminary aerodynamic database of a next generation launch vehicle as input for performances evaluations as well as launcher control, sizing, and staging. In this framework, different design approaches are considered. Indeed, steady computational fluid dynamics (CFD), with both Euler and Navier-Stokes approximations, are carried out to assess launcher aerodynamics. On the other hand, a coupled approach between unsteady CFD and a six degree-of-freedom trajectory analysis are exploited to address booster separation dynamics at staging conditions.
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