The viscous, three-dimensional flowfield of a lifting helicopter rotor in hover is calculated by using an upwind, implicit, finite-difference numerical method for solving the thin layer Navier-Stokes equations. The induced effects of the wake, including the interaction of tip vortices with successive blades, are calculated as part off the overall flowfield solution without using any ad hoc wake models. Comparison of the numerical results for the subsonic and transonic conditions show good agreement with the experimental data and with the previously published Navier-Stokes calculations using a simple wake model. Some comparisons with Euler calculations are also presented, along with some discussions of the grid refinement studies.


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    Titel :

    Flowfield of a lifting rotor in hover - A Navier-Stokes simulation


    Beteiligte:
    Srinivasan, G. R. (Autor:in) / Baeder, J. D. (Autor:in) / Obayashi, S. (Autor:in) / Mccroskey, W. J. (Autor:in)

    Erschienen in:

    AIAA Journal ; 30 , 10


    Erscheinungsdatum :

    1992-10-01



    Medientyp :

    Sonstige


    Format :

    Keine Angabe


    Sprache :

    Englisch


    Schlagwörter :


    Flowfield of a lifting rotor in hover - A Navier-Stokes simulation

    SRINASAN, G. R. / JAI Associates / Inc. et al. | AIAA | 1992


    Flowfield of a lifting rotor in hover: A Navier-Stokes simulation

    Srinivasan, G.R. / Baeder, J.D. / Obayashi, S. et al. | Tema Archiv | 1992



    Flowfield analysis of modern helicopter rotors in hover by Navier-Stokes method

    Srinivasan, G.R. / Raghavan, V. / Duque, E.P.N. et al. | Tema Archiv | 1993