Large Transport Aircraft Wake Vortex Affected by Vortex Devices
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.
KeywordsReference Configuration Wake Vortex Merging Process Axial Vorticity Peak Vorticity
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