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Navier-Stokes High-Lift Airfoil Computations with Automatic Transition Prediction Using the DLR TAU Code

  • A. Krumbein
  • N. Krimmelbein
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)

Abstract

A Reynolds-averaged Navier-Stokes solver, a laminar boundary-layer code and different transition prediction methods for the prediction of Tollmien-Schlichting and cross flow instabilities were coupled for the automatic prediction of laminar-turbulent transition on general 3-dimensional aircraft configurations during the ongoing flow computation. The procedure is applied to a two-dimensional three-element high-lift airfoil configuration which is characterized by the existence of laminar separation bubbles using different operation modes of the procedure.

Keywords

Transition Location Separation Bubble Transition Prediction Mode Combination Laminar Separation Bubble 
These keywords were added by machine and not by the authors. This process is experimental and the keywords may be updated as the learning algorithm improves.

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Copyright information

© Springer-Verlag Berlin Heidelberg 2007

Authors and Affiliations

  • A. Krumbein
    • 1
  • N. Krimmelbein
    • 2
  1. 1.Deutsches Zentrum für Luft-und Raumfahrt e.V., AS-NVGöttingenGermany
  2. 2.Technical University of Braunschweig, ISMBraunschweigGermany

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