Wall Effects and Corner Separations for Subsonic and Transonic Flow Regimes

  • Alexander Klein
  • Sebastian Illi
  • Klemens Nübler
  • Thorsten Lutz
  • Ewald Krämer

Abstract

Corner flow effects prove to have a significant influence on the results obtained in wind tunnels. During the SCBOPT project discrepancies between experiments and numerical investigations occurred. 3D numerical studies considering the wind tunnel were performed to show the effect of wind tunnel walls on the obtained results in both subsonic and transonic flows. The subsonic simulation of the DNW-TWG wind tunnel is presented within this report. Further investigations of a wing fuselage intersection were conducted to investigate the effect of corner separation near the trailing edge. It is shown that the presence of the fuselage does not only have a local effect in the vicinity of the corner separation but influences the complete flow around the wing.

Keywords

Wind Tunnel Turbulence Model Separation Bubble Wall Effect Normal Shock 
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 2012

Authors and Affiliations

  • Alexander Klein
    • 1
  • Sebastian Illi
    • 1
  • Klemens Nübler
    • 1
  • Thorsten Lutz
    • 1
  • Ewald Krämer
    • 1
  1. 1.Institute of Aerodynamics and Gas DynamicsUniversity of StuttgartStuttgartGermany

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