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Wall Effects and Corner Separations for Subsonic and Transonic Flow Regimes

In: High Performance Computing in Science and Engineering '11

Author

Listed:
  • Alexander Klein

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

  • Sebastian Illi

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

  • Klemens Nübler

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

  • Thorsten Lutz

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

  • Ewald Krämer

    (University of Stuttgart, Institute of Aerodynamics and Gas Dynamics)

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.

Suggested Citation

  • Alexander Klein & Sebastian Illi & Klemens Nübler & Thorsten Lutz & Ewald Krämer, 2012. "Wall Effects and Corner Separations for Subsonic and Transonic Flow Regimes," Springer Books, in: Wolfgang E. Nagel & Dietmar B. Kröner & Michael M. Resch (ed.), High Performance Computing in Science and Engineering '11, edition 127, pages 393-407, Springer.
    • Handle: RePEc:spr:sprchp:978-3-642-23869-7_29
    DOI: 10.1007/978-3-642-23869-7_29
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