Summary
The results of a wind tunnel investigation on the wake vortex evolution behind a half-model of a four-engined large transport aircraft in high-lift configuration, with and without vortex devices, are presented. The wake is measured by means of advanced hot-wire anemometry up to 5.6 span distances downstream of the model. Results obtained include velocity, vorticity and turbulence intensity fields. The measured data are evaluated in order to establish and test possible wake vortex strength alleviation strategies.
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References
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© 2004 Springer-Verlag Berlin Heidelberg
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Bellastrada, C., Breitsamter, C. (2004). Large Transport Aircraft Wake Vortex Affected by Vortex Devices. In: Breitsamter, C., Laschka, B., Heinemann, HJ., Hilbig, R. (eds) New Results in Numerical and Experimental Fluid Mechanics IV. Notes on Numerical Fluid Mechanics and Multidisciplinary Design, vol 87. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-39604-8_1
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DOI: https://doi.org/10.1007/978-3-540-39604-8_1
Publisher Name: Springer, Berlin, Heidelberg
Print ISBN: 978-3-642-53546-8
Online ISBN: 978-3-540-39604-8
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