The effects of RSRA fuselage configurations on rotor performance and loads have been quantified analytically by means of currently available potential flow and rotor analysis. Four configurations of the Rotor Systems Research Aircraft (RSRA) were considered in this study. They were: (1) fuselage alone (conventional helicopter); (2) fuselage with auxiliary propulsion; (3) fuselage with wings (auxiliary lift); and (4) fuselage with both auxiliary lift propulsion. The rotor system investigated was identical to a CH-47D front rotor except that it had four instead of three blades. Two scaled-down versions of the same rotor were also analyzed to determine the effect of rotor scale on the fuselage upwash effects. The flight conditions considered for the upwash study are discussed. The potential flow models for the RSRA configuration, with and without the wings and the auxiliary propulsion system, are presented. The results of fuselage/wing/propulsion system upwash on performance and loads are also presented.


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    Title :

    Fuselage upwash effects on RSRA rotor systems


    Contributors:
    Cowan, J. (author) / Dadone, L. (author)

    Publication date :

    1985-08-01


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English


    Keywords :


    Fuselage Upwash Effects on RSRA Rotor Systems

    J. Cowan / L. Dadone | NTIS | 1985


    Rotor Systems Research Aircraft (RSRA)

    Condon, G. W. / Letchworth, R. | NTRS | 1976


    Flight Testing the Rotor Systems Research Aircraft (RSRA)

    G. W. Hall / R. K. Merrill | NTIS | 1983



    Flight testing the Rotor Systems Research Aircraft (RSRA)

    Merrill, R. K. / Hall, G. W. | NTRS | 1982