Method is presented for computing downwash field due to vortex wake of lifting rotor in forward flight; formulation permits calculation of velocities at arbitrary points in space; suitable choice of computation points thus permits treatment of isolated or tandem rotor problems; calculations have been carried out for single and tandem rotors tested by NASA, and computed airloads are compared to experimental data; reasonable agreement is shown.


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    Title :

    Aerodynamic characteristics of model helicopter rotor operating under nominally stalled conditions in forward flight


    Additional title:

    Am Helicopter Soc -- J


    Contributors:


    Publication date :

    1964


    Size :

    8 pages


    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English


    Keywords :


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