Abstract

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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