An experimental investigation of leading-edge flow separation from a 4 per cent thick two-dimensional biconvex aerofoil

dc.contributor.author	B. D. Henshall	en_US
dc.contributor.author	R. F. Cash	en_US
dc.date.accessioned	2014-10-21T15:54:39Z
dc.date.available	2014-10-21T15:54:39Z
dc.date.issued	1957	en_US
dc.identifier.other	ARC/R&M-3091	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3662
dc.description.abstract	The development of leading-edge flow separation as incidence is raised, for a 4 per cent thick twodimensional biconvex aerofoil, was studied experimentally for wide ranges of incidence at Mach numbers of 0.40, 0.50, 0.60 and 0.70. Pressure distributions and flow photographs are presented which illustrate the growth of the 'bubble' of separated flow.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	An experimental investigation of leading-edge flow separation from a 4 per cent thick two-dimensional biconvex aerofoil	en_US