Abstract This paper deals with the aerodynamic and aerothermodynamic design analysis of a conceptual aeroshape, designed to fit the constraints of VEGA launcher fairing and with the capability to perform an end-to-end mission from launch, orbit keeping, re-entry and landing on conventional runway. Aerodynamic and aerothermodynamic performances of the aeroshape under investigation were evaluated for the whole flight scenario by means of several numerical tools as low-order methods and computational fluid dynamics code. Results are provided in the paper and considered applicable to drive the choice of a more suitable aeroshape for a whole re-entry system development.
Aerodynamic and Aerothermodynamic Design of the USV3 Re-Entry Vehicle
Aerotecnica Missili & Spazio ; 94 , 3 ; 145-160
01.07.2015
16 pages
Aufsatz (Zeitschrift)
Elektronische Ressource
Englisch
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