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.


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    Title :

    Aerodynamic and Aerothermodynamic Design of the USV3 Re-Entry Vehicle


    Contributors:

    Published in:

    Publication date :

    2015-07-01


    Size :

    16 pages




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English




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