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Wing-Tip Vortex / Jet Interaction in the Extended Near Field

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High Performance Computing in Science and Engineering '08

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Summary

The vortex wake behind a half wing is spatially simulated up to the extended near field. Instabilities of the wing tip vortex are analyzed. Results from wind tunnel measurements are used as inflow boundary conditions for an LES of the wake region. An aircraft engine is modeled in the experimental setup, where the jet is driven by pressurized air. The engine was mounted in two different positions under the wing model to investigate the influence of the location of the engine jet on the vortex wake. The numerical simulations of the wake were able to predict trajectories and instabilities of the vortex core. A position of the engine towards the root of the wing created a smaller deflections of the vortex.

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Authors and Affiliations

  1. Institute of Aerodynamics, RWTH Aachen University, Wüllnerstr. 5a, 52062, Aachen, Germany

    Frank T. Zurheide, Matthias Meinke & Wolfgang Schröder

Authors
  1. Frank T. Zurheide
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  2. Matthias Meinke
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  3. Wolfgang Schröder
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Editor information

Wolfgang E. Nagel Dietmar B. Kröner Michael M. Resch

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© 2009 Springer-Verlag Berlin Heidelberg

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Zurheide, F.T., Meinke, M., Schröder, W. (2009). Wing-Tip Vortex / Jet Interaction in the Extended Near Field. In: Nagel, W.E., Kröner, D.B., Resch, M.M. (eds) High Performance Computing in Science and Engineering '08. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-88303-6_20

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