Aerodynamic performances and noise at take-off conditions are predicted by two different aerodynamic codes developed by the authors and evaluated with the wind tunnel results. The extended lifting line theory named as LCM is a quick code and proved to be a useful tool for predicting the preliminary design data of propeller component on performance and noise. Another feature of this code is the ability to deal with the case of finite shaft angle of attack. The predicted increment of ground noise level is shown to agree well with the measurement. The full Navier-Stokes code demonstrated the capability to simulate the flow field around the propeller such as the leading edge vortex at high blade angle, the horseshoe vortex at blade root, or the boundary layer development. The computed noise using this code to obtain source intensity distribution coincides well with LCM results, which means that the linear potential source modeling is good enough in this speed range.


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    Title :

    Predicted flow field around the advanced propeller at take-off


    Additional title:

    Vorausberechnetes Stroemungsfeld um einen fortschrittlichen Propeller beim Abflug


    Contributors:
    Saito, S. (author) / Kobayashi, H. (author) / Nakamura, Y. (author) / Matsuo, Y. (author)

    Published in:

    AIAA-Papers ; Jul ; 1-7


    Publication date :

    1988


    Size :

    7 Seiten, 15 Bilder, 11 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Predicted flow field around the advanced propeller at take-off

    SAITO, SHIGERU / KOBAYASHI, HIROSHI / NAKAMURA, YOSHIYA et al. | AIAA | 1988