Study to determine division of aerodynamic loads between shroud and propeller; propeller contribution to overall normal force and pitching moment of VTOL configuration was found to be relatively small for stalled or unstalled shroud; ratio of thrust of propeller and spinner to total thrust was found to vary from 0.4 in hovering to 0.7 at highest advance ratio of tests, 0.595, with shroud at zero angle of attack.


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    Title :

    Aerodynamic loads on isolated shrouded-propeller configuration for angles of attack from -10°


    Additional title:

    NASA -- Tech Notes


    Contributors:


    Publication date :

    1962


    Size :

    29 pages


    Type of media :

    Report


    Type of material :

    Print


    Language :

    English


    Keywords :