The effects of rotor wake on helicopter fuselage aerodynamic characteristics were investigated in the Langley V/STOL tunnel. Force, moment, and pressure data were obtained on three fuselage models at various combinations of windspeed, sideslip angle, and pitch angle. The data show that the influence of rotor wake on the helicopter fuselage yawing moment imposes a significant additional thrust requirement on the tail rotor of a single-rotor helicopter at high sideslip angles. (Author)


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    Title :

    Wind Tunnel Investigation of Helicopter-Rotor Wake Effects on Three Helicopter Fuselage Models


    Contributors:
    J. C. Wilson (author) / R. E. Mineck (author)

    Publication date :

    1975


    Size :

    209 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English