Two noncircular cross-section bodies and a high wing-body configuration at incidence in a low subsonic free stream

Pantelatos, DK; Tzotzolakis, DC; Mathioulakis, DS

dc.contributor.author	Pantelatos, DK	en
dc.contributor.author	Tzotzolakis, DC	en
dc.contributor.author	Mathioulakis, DS	en
dc.date.accessioned	2014-03-01T01:29:25Z
dc.date.available	2014-03-01T01:29:25Z
dc.date.issued	2008	en
dc.identifier.issn	0889-9746	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/19255
dc.subject	non-axisymmetric body	en
dc.subject	asymmetric loading	en
dc.subject	cross-flow vortices	en
dc.subject	NACA4415 airfoil	en
dc.subject	high-wing configuration	en
dc.subject	UAV	en
dc.subject.classification	Engineering, Mechanical	en
dc.subject.classification	Mechanics	en
dc.title	Two noncircular cross-section bodies and a high wing-body configuration at incidence in a low subsonic free stream	en
heal.type	journalArticle	en
heal.identifier.primary	10.1016/j.jfluidstructs.2007.12.009	en
heal.identifier.secondary	http://dx.doi.org/10.1016/j.jfluidstructs.2007.12.009	en
heal.language	English	en
heal.publicationDate	2008	en
heal.abstract	This experimental study examines the flow characteristics over a square cross-section body with sharp edges, a rectangular one with rounded edges, and a high wing-body configuration, in a low subsonic free stream. Pressure, velocity, force measurements and flow visualization provide a picture of the flow behaviour, locally and globally. Flow visualization and velocity measurements clearly depict the presence of two axial counter-rotating vortices in the leeside of the first two bodies, being mainly responsible for the asymmetric loading at nonzero roll angles, maximizing the side-force at a roll angle of about 25 degrees. For all body orientations there is always a recirculation region at the nose-afterbody junction leeside area, the extent of which depends mainly on the roll angle. Pressure gradients take high values at the corners of the after body cross-section, even when these are rounded. No asymmetries were practically detected for a zero roll angle and pitch angles up to 20 degrees for the examined three models. The wing-body configuration exhibits a higher lift slope and a more negative zero lift angle, compared to the wing-alone case, and the side-force increases monotonically with the roll angle, without showing any maximum in contrast to the other two models. (C) 2008 Elsevier Ltd. All rights reserved.	en
heal.publisher	ACADEMIC PRESS LTD ELSEVIER SCIENCE LTD	en
heal.journalName	JOURNAL OF FLUIDS AND STRUCTURES	en
dc.identifier.doi	10.1016/j.jfluidstructs.2007.12.009	en
dc.identifier.isi	ISI:000259372000002	en
dc.identifier.volume	24	en
dc.identifier.issue	6	en
dc.identifier.spage	778	en
dc.identifier.epage	798	en