Spatial vortex-separation structure and airplane lifting surface interaction control

Aircraft Engineering


Аuthors

Svirshchevsky S. B., Artamonova L. G., Radtsig A. N., Semenchikov N. V.*

Moscow Aviation Institute (National Research University), 4, Volokolamskoe shosse, Moscow, А-80, GSP-3, 125993, Russia

*e-mail: semenchikovnv@rambler.ru

Abstract

Experimental investigations of composite spatial separation flows in leeward and upper parts of airfoils, wings and systems of wings at low and high attack angles have been carried out in subsonic wind tunnels at the MAI. Wide application feasibility is shown for span-wise baffles to control flow separation and increase lift properties of various configurations. Spatial structure examination of flow around tandem scheme has shown the configuration of baseline wing with a forward horizontal tail can be efficiently used for favorable interference in vortex systems, i.e. to increase lift of the configurations and to decrease airframe acoustic load.

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