Prediction of flight performance has been dependent upon sea-level data that must be extrapolated to flight configuration; errors up to 4% in predicted specific impulse resulted because of inability to identify factors affecting extrapolation; technique permits estimation of specific impulse within 2% for conventional propellant systems at any exit area ratio with no test data; if sea-level test data are available, altitude performance can be estimated within 1%; effects of mixture ratio-distribution and interactions between injector chamber performance and nozzle are responsible for most of errors using characteristic velocity-thrust coefficient method.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Improved method for rocket performance prediction


    Additional title:

    J Spacecraft Rockets


    Contributors:
    Valentine, R.S. (author) / Dean, L.E. (author) / Pieper, J.L. (author)

    Published in:

    Publication date :

    1966


    Size :

    6 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


    An improved method for rocket performance prediction.

    DEAN, L. E. / PIEPER, J. L. | AIAA | 1966


    Rocket Performance Prediction Technique

    J. H. Morgenthaler / W. R. Stepien | AIAA | 1975


    Hybrid Rocket Propulsion Performance Prediction

    Cavalleri, R. J. / Loehr, R. D. / American Institute of Aeronautics and Astronautics et al. | British Library Conference Proceedings | 2005


    Solid rocket performance prediction techniques

    COHEN, N. / HARRY, III, D. / PRICE, C. et al. | AIAA | 1974


    Hybrid Rocket Propulsion Performance Prediction

    Cavalleri, Robert / Loehr, Richard | AIAA | 2005