Numerical calculations for the counter rotation propeller (CRP) have been performed using the newly developed aerodynamic code which incorporates basically a curved lifting line theory and two-dimensional airfoil data. This code, named as local circulation method (LCM), is originally developed for the application to helicopter rotors, and extended here to be able to cope with CRP rotors which have highly skewed (swept blade systems operating in high subsonic or transonic range. Extensive calculations on CRP performance in wide range of geometrical and operational rotor variables provided the design data base including efficiency maps parametered by blade pitch angles of front and rear rotor. It should be noted that the present code needs less time (15 sec. by FACOM 780) without losing the level of accuracy compared with other method such as the vortex theory and thus demonstrated the capability as a design tool for CRP. The other capability can be seen in the computation in rather complicated cases such as yawed flight (or aircraft with finite angle of attack), gust penetration, or maneuvered flight. As an example, asymmetric load distribution over the rotor disks (front and rear) or the time history of bending moment at the blade root of the CRP flying in the cross wind was calculated.


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    Title :

    Performance calculation of counter rotation propeller


    Additional title:

    Berechnung der Leistung eines gegendrehenden Propellers


    Contributors:
    Saito, S. (author) / Kobayeshi, H. (author) / Nasu, K. (author) / Nakamura, Y. (author)

    Published in:

    AIAA-Papers ; Jul ; 1-8


    Publication date :

    1987


    Size :

    8 Seiten, 14 Bilder, 12 Quellen


    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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