A direct panel method based on a novel boundary integral formulation for the velocity potential is presented and applied to helicopter rotors experiencing blade-vortex interaction (BVI). It avoids the numerical instabilities arising in the standard direct panel method in case of blade/wake impingement. This aerodynamic formulation yields a unified approach for the calculation of free-wake evolution and the blade-pressure field; it is fully 3-D, includes bodythickness effects, and can be applied to blades with arbitrary shape and motion. Blade-pressure predictions and the corresponding acoustic fields correlate well with wind-tunnel test data for helicopter rotors in descent flight, in which severe blade-vortex interaction occurs.


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    Title :

    Novel boundary integral formulation of blade-vortex interaction aerodynamics of helicopter rotors


    Additional title:

    Neue Randintegralformulierung für die Aerodynamik der Rotor-Wirbel-Wechselwirkung von Helikopterrotoren


    Contributors:

    Published in:

    AIAA Journal (online) ; 45 , 6 ; 1169-1176


    Publication date :

    2007


    Size :

    8 Seiten, 18 Bilder, 24 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English