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.
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Klein, A., Illi, S., Nübler, K., Lutz, T., Krämer, E. (2012). Wall Effects and Corner Separations for Subsonic and Transonic Flow Regimes. In: Nagel, W., Kröner, D., Resch, M. (eds) High Performance Computing in Science and Engineering '11. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-642-23869-7_29
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DOI: https://doi.org/10.1007/978-3-642-23869-7_29
Publisher Name: Springer, Berlin, Heidelberg
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