Tunnel-wall effect on an aerofoil at subsonic speeds

dc.contributor.author	A. Thom	en_US
dc.contributor.author	Laura Klanfer	en_US
dc.date.accessioned	2014-10-21T15:53:15Z
dc.date.available	2014-10-21T15:53:15Z
dc.date.issued	1951	en_US
dc.identifier.other	ARC/R&M-2851	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3407
dc.description.abstract	This is a detailed study of the effect of the presence of walls on the flow past a symmetrical aerofoil at zero incidence. The low-speed case is considered first, followed by solutions at a Mach number of 0.7. The methods used are essentially arithmetical, but a new approach is used for the compressible case. The manner in which the walls affect the pressure distribution is clearly shown.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Tunnel-wall effect on an aerofoil at subsonic speeds	en_US