A large amount of data to determine plume effects have been obtained from various simulation techniques. To provide data for evaluating the adequacy of these simulations, a test utilizing a rocket sled to measure surface pressures on a full-size, live, high thrust rocket at Mach number up to Moo 1.6. Selected portions of the data are presented to show Mach number and thrust level effects.


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    Titel :

    Investigation of Plume Induced Separation on a Full-Size Missile at Supersonic Velocities


    Beteiligte:
    T. A. Martin (Autor:in)

    Erscheinungsdatum :

    1980


    Format / Umfang :

    26 pages


    Medientyp :

    Report


    Format :

    Keine Angabe


    Sprache :

    Englisch