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.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

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


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Nelson, R.E. (author) / Patmor, G.O. (author) / McFarland, B.L. (author) / Mandell, B. (author)

    Published in:

    Publication date :

    1964


    Size :

    4 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    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