A Navier Stokes and a potential method are used to compute the pressure distributions around a generic helicopter fuselage. In addition, the potential method is coupled with 3 different rotor models and the resulting time-averaged fuselage pressures are compared to experimental values for various operating conditions. For the isolated body, it is demonstrated that both potential and Navier Stokes methods give similar values for fuselage pressure, but the Navier Stokes method calculates viscous phenomena from first principles. It is also demonstrated that when the potential method is coupled with a simple impeller rotor model, calculated fuselage pressures correlate well with time averaged experimental values over regions of attached, non-vortical flow.


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    Title :

    The application of CFD to helicopter flowfields


    Additional title:

    Anwendung der rechnergestützten Strömungsmechanik auf Hubschrauber-Strömungsfelder


    Contributors:
    Vyriotes, P. (author) / Khalid, M. (author)


    Publication date :

    1996


    Size :

    8 Seiten, 11 Bilder, 17 Quellen



    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English