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Aspects of the Modeling and Numerical Simulation of Leading-Edge Vortex Flow

  • H. W. M. Hoeijmakers
Conference paper
Part of the International Union of Theoretical and Applied Mechanics book series (IUTAM)

Summary

A cell-centered central-difference finite-volume Euler method is applied to the steady subsonic flow about a 65-deg sharp-edged cropped delta wing at incidences close to the incidence at which leading-edge vortex breakdown is observed in wind tunnel experiments. Above a critical value of the incidence the pseudo-time dependent numerical procedure fails to attain a steady-state solution. For the case of subsonic leading-edge vortex flow the occurrence of “solution breakdown” indicates the limits of the domain of applicability of the steady-flow Euler method. In the search for the critical incidence it is found that for a given grid and for a given setting of the parameters controlling the artificial dissipation two distinct, steady-state solutions exist. Analysis of the two solutions obtained at one incidence reveals that within the vortex core above the aft part of the wing these solutions feature remarkably different velocity and vorticity distributions.

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Copyright information

© Springer-Verlag Berlin Heidelberg 1993

Authors and Affiliations

  • H. W. M. Hoeijmakers
    • 1
  1. 1.National Aerospace LaboratoryNLRAmsterdamThe Netherlands

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