Upper-stage rocket engines with large area ratio nozzles must be tested under simulated altitude conditions during development; experiment conducted to determine operational and heat-transfer characteristics of rocket engine altitude-simulation ejector systems for such testing; constant-area and second-throat types were tested; both types, with 90° turns required higher engine chamber pressures to obtain ejector system start than geometrically similar straight systems; other findings.


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    Titel :

    Scale model testing of 90° supersonic turn ejector systems for altitude simulation


    Weitere Titelangaben:

    J Spacecraft Rockets


    Beteiligte:
    Nelson, R.E. (Autor:in) / Patmor, G.O. (Autor:in) / McFarland, B.L. (Autor:in) / Mandell, B. (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    1964


    Format / Umfang :

    4 pages


    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch


    Schlagwörter :



    SCALE MODEL TESTING OF 90 DEG TURN EJECTOR SYSTEMS FOR ROCKET ENGINE ALTITUDE SIMULATION

    Mandell, B. / Mc Farland, B. L. / Nelson, R. E. et al. | NTRS | 1963


    SCALE MODEL TESTING OF 90 DEG TURN EJECTOR SYSTEMS FOR ROCKET ENGINE ALTITUDE SIMULATION

    Mandell, B. / Mc Farland, B. L. / Nelson, R. E. et al. | NTRS | 1963


    SCALE MODEL TESTING OF 90 DEG TURN EJECTOR SYSTEMS FOR ROCKET ENGINEALTITUDE SIMULATION

    NELSON, R. / PATMOR, G. / MCFARLAND, B. et al. | AIAA | 1963