Summary
Wind tunnel investigations have been performed to study the effect of different span loadings, obtained by means of differential flap settings, on the structure of the wake vortex behind a half-model of a four-engine large transport aircraft. Advanced hot-wire anemometry technique has been used to measure the wake vortex velocities at five cross stations up to 4.5 span distances downstream of the model. Results obtained are analysed to identify possible benefits in terms of alleviation of the wake vortex hazard.
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© 2006 Springer-Verlag Berlin Heidelberg
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Bellastrada, C., Breitsamter, C. (2006). Effect of Differential Flap Settings on the Wake Vortex Evolution of Large Transport Aircraft. In: Rath, HJ., Holze, C., Heinemann, HJ., Henke, R., Hönlinger, H. (eds) New Results in Numerical and Experimental Fluid Mechanics V. Notes on Numerical Fluid Mechanics and Multidisciplinary Design (NNFM), vol 92. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-33287-9_4
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DOI: https://doi.org/10.1007/978-3-540-33287-9_4
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-540-33286-2
Online ISBN: 978-3-540-33287-9
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