Studies made at Rocket Propulsion Establishment of Ministry of Aviation to determine relationship between specific weight and thrust of liquid bi-propellant rocket engine; it is concluded that minimum specific weight is achieved at thrust level near 50,000 lb; difference in specific weight between engines of 200,000 and 50,000 lb thrust is only about 10% and this is shown to be equivalent to only 1% in propellant specific impulse.


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    Title :

    Optimum size of rocket engine


    Additional title:

    Roy Aeronautical Soc -- J


    Contributors:

    Published in:

    Publication date :

    1960


    Size :

    26 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :



    Some optimum rocket trajectories

    Leitmann, G. | Engineering Index Backfile | 1961


    Some optimum rocket trajectories

    Leitmann, G. | Engineering Index Backfile | 1961



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