Experimental flow study over a blunt-nosed axisymmetric body at incidence

Pantelatos, DK; Mathioulakis, DS

dc.contributor.author	Pantelatos, DK	en
dc.contributor.author	Mathioulakis, DS	en
dc.date.accessioned	2014-03-01T01:20:27Z
dc.date.available	2014-03-01T01:20:27Z
dc.date.issued	2004	en
dc.identifier.issn	0889-9746	en
dc.identifier.uri	https://dspace.lib.ntua.gr/xmlui/handle/123456789/15933
dc.subject	Flow Visualization	en
dc.subject	Pressure Distribution	en
dc.subject	Liquid Crystal	en
dc.subject	Wall Shear Stress	en
dc.subject.classification	Engineering, Mechanical	en
dc.subject.classification	Mechanics	en
dc.subject.other	SEPARATION PATTERNS	en
dc.subject.other	HEMISPHERE CYLINDER	en
dc.subject.other	REYNOLDS-NUMBERS	en
dc.subject.other	BOUNDARY-LAYER	en
dc.subject.other	LAMINAR	en
dc.subject.other	TOPOLOGY	en
dc.title	Experimental flow study over a blunt-nosed axisymmetric body at incidence	en
heal.type	journalArticle	en
heal.identifier.primary	10.1016/j.jfluidstructs.2004.07.004	en
heal.identifier.secondary	http://dx.doi.org/10.1016/j.jfluidstructs.2004.07.004	en
heal.language	English	en
heal.publicationDate	2004	en
heal.abstract	The flowfield over a blunt-nosed cylinder was examined experimentally at a low subsonic speed for Re = 1.88 x 10(5) and angles of attack up to 40degrees. Velocity measurements were carried out (employing a seven-hole Pitot tube) as well as wall static pressure and wall shear-stress measurements. Surface flow visualization was applied using liquid crystals and a mixture of oil-TiO2. For all the examined cases no flow asymmetries were found. For high angles of attack (20degrees and above) a separation "bubble" appears at the leeside of the nose area (streamwise flow separation). The basic feature of the circumferential pressure distribution at the after body area for these angles of attack is a plateau close to the suction peak and a fast recovery next to it. One streamwise vortex on each side of the symmetry plane is formed as well as a separation bubble about 90degrees far from this plane, where the cross-flow primary separation line is located. Each cross-flow primary separation line starts at the leeside nose area and moves towards the windward side along the cylindrical after body. The space between the two primary separation lines close to the wall is characterized by high flow fluctuations on the leeside, compared to the low fluctuations of the windward side. (C) 2004 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.2004.07.004	en
dc.identifier.isi	ISI:000225512600005	en
dc.identifier.volume	19	en
dc.identifier.issue	8	en
dc.identifier.spage	1103	en
dc.identifier.epage	1115	en