Overview of the VEGA-E space launcher model aerodynamic and aeroacoustic environment

The aerodynamic and aeroacoustic loads acting on the new European launcher VEGA-E were investigated through dedicated wind tunnel tests and numerical simulations performed over a wide range of Mach numbers, in order to cover the dense atmosphere flight trajectory from subsonic to supersonic conditions. The tests were performed on specifically designed models with all protrusions installed (wiring tunnels, RACS, retrorockets fairings). The instrumented model featured a six-component balance, 64 pressure taps and 24 fluctuating pressure transducers, strategically positioned along the model surface. The wind tunnel experiments and the RANS CFD simulations carried out in wind tunnel conditions synergistically contribute to the aerodynamic database. Some significant examples are illustrated, in order to highlight the key flow features and to verify the fidelity of the comparison between numerical and experimental results. The focus of this work is the description of the peculiar flow characteristics, based on the measurement of forces, moments and static and fluctuating pressure distribution. The flow feature interpretation is also supported by oil flow visualizations and Schlieren images. • The aerodynamic and aeroacoustic environment around the VEGA-E launcher was assessed through CFD and WT measurements. • Experiments concerned forces and moments, static and fluctuating pressure, Schlieren and oil-flow visualisations. • Parameters tested included Mach numbers in the range 0.5-3, pitch angles from 0 ∘ to 10 ∘ and different roll angles. • CFD was performed by means of RANS simulations using ANSYS Fluent®. • Numerical results in terms of forces, moments, static pressure and flow field were compared with the experiments.