The Japan Aerospace Exploration Agency (JAXA) recently proposed a landing mission to Mars. To improve the feasibility of the mission, rarefied aerodynamics need to be accurately estimated for a precise determination of its flight path and landing site. This work has investigated rarefied hypersonic aerodynamics experimentally and numerically. A rarefied aerodynamic measurement scheme has been developed by using pendulous models in a hypersonic rarefied wind tunnel at JAXA, and the results have been compared with direct simulation Monte Carlo computations. Consequently, numerically predicted aerodynamic coefficients are consistent with the measured values.


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    Titel :

    Aerodynamic Measurements and Computational Analyses in Hypersonic Rarefied Flows


    Beteiligte:
    Ozawa, T. (Autor:in) / Suzuki, T. (Autor:in) / Fujita, K. (Autor:in)

    Erschienen in:

    AIAA Journal ; 53 , 11 ; 3327-3337


    Erscheinungsdatum :

    01.11.2015




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch