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.
Base-Pressure Experimental Investigation on a Space Launcher in Subsonic Regime
Journal of Spacecraft and Rockets ; 50 , 3 ; 572-578
01.05.2013
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
Base-Pressure Experimental Investigation on a Space Launcher in Subsonic Regime
Online Contents | 2013
|Subsonic Base Pressure Fluctuations
AIAA | 1979
|Online Contents | 2000
Online Contents | 2001
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