03.1 - Aerodynamics - CFD Methods and Validation
LAUNCHER AERODYNAMIC ANALYSIS WITH PLUME EFFECTS
A. Viviani, University of Campania, Italy; G. Pezzella, Italian Aerospace Research Centre, Italy
The paper reports on the CFD results of design analyses of a next generation expendable launcher. The vehicle features a hummer head cylinder main body with two boosters. The primary work aim is the flow simulation of the vehicle during ascent with and without rocket plume to address this effect in the preliminary aerodynamic database of the launcher. This numerical investigation integrates the aerodynamic appraisal of the launcher carried out so far and summarized in several research contributions. In this framework, full 3-D CFD analyses have been extensively performed between Mach 0.5 and 5. The rocket plume is accounted in the simulation by means of a proper boundary condition at launcher/booster base.