The flow field generated by a helicopter in flight is extremely complex and it has been recognized that interactions between different components can significantly affect helicopter performance. In particular, the effects of the interaction between the rotor wake and the helicopter fuselage are extremely difficult to predict and pose a challenging problem for researchers and designers in the rotorcraft area. In the present work, a model for the interaction of a rotor-tip-vortex with the airframe of a helicopter is developed. The present report describes the calculation of the motion of the tip-vortex toward the airframe, the calculation of the induced pressure on the airframe, and the calculation of the boundary-layer flow under the vortex during the time period prior to the time when a portion of the tip-vortex collides with the airframe.


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    Title :

    Boundary Layers Induced by Three-Dimensional Vortex Loops


    Contributors:
    A. T. Conlisk (author) / H. Affes (author) / O. R. Burggraf (author) / Z. Xiao (author)

    Publication date :

    1993


    Size :

    278 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Adaptive grid scheme for vortex-induced boundary layers

    Adams, E. C. / Conlisk, A. T. / Smith, F. T. | AIAA | 1995