Abstract
An experimental investigation of the space launcher base flow during the early ascent phases has been carried out in a subsonic wind tunnel. Specifically, this study has considered a simple launcher model formed by a circular cylinder with an ogival nose and a centered nozzle in the truncated base. Tests have been conducted generating subsonic streams in the wind-tunnel test section ranging from Mach 0.18 to 0.43 and an overexpanded Mach 3 cold jet through the nozzle. Static pressure probes located on the launcher side walls and base provided the pressure distribution data. The analysis of the experimental data features the “aspiration” effects caused by the supersonic jet on the external subsonic stream and on the base pressure.
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