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Simulation of Oscillating Airfoils and Moving Flaps Employing the DLR-TAU Unsteady Grid Adaptation

  • A.D. Gardner
  • K. Richter
  • H. Rosemann
Part of the Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM) book series (NNFM, volume 96)

Abstract

The use of unsteady adaptation with the DLR-TAU Navier-Stokes solver is presented as a method of improving the modelling of flows where the aerodynamic performance of a body is determined by the action of moving localised regions of high-gradient flow. Examples are presented of transonic limit cycle oscillation and dynamic stall. First results indicate that good grid convergence can be achieved without necessarily requiring that the flow around the specific airfoil is well understood in advance.

Keywords

Reynolds Average Navier Stoke Reynolds Average Navier Stoke Aerodynamic Performance Pitching Moment Grid Convergence 
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.D. Gardner
    • 1
  • K. Richter
    • 1
  • H. Rosemann
    • 1
  1. 1.DLR AS-HKGöttingenGermany

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