Simulation experiments were performed in the NASA Langley Full Scale Tunnel to investigate the retroplume heating rates encountered by a lander vehicle during a terminal descent to a planetary surface. A 10% scale model of the Viking Lander with freestream velocity conditions from 37 to 75 ft/sec was used for simulation. The simulation test data were close to the theoretical predictions of Hill et al. (1971).


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    Titel :

    Penetration of retrorocket exhausts into subsonic counterflows.


    Beteiligte:
    Jarvinen, P. O. (Autor:in) / Hill, J. A. F. (Autor:in)


    Erscheinungsdatum :

    1973-01-01


    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Penetration of retrorocket exhausts into subsonic counterflows.

    JARVINEN, P. O. / HILL, J. A. F. | AIAA | 1973


    Parachute Retrorocket Airdrop System

    J. L. Michal / J. L. Oates / A. L. Martinez | NTIS | 1970



    Supercritical Combustion of General Fluids in Laminar Counterflows

    Wang, X. / Huo, H. / Yang, V. et al. | British Library Conference Proceedings | 2013