The calculation of the profile drag of aerofoils

dc.contributor.author	H. B. Squire
dc.contributor.author	A. D. Young
dc.date.accessioned	2014-10-21T12:03:23Z
dc.date.available	2014-10-21T12:03:23Z
dc.date.issued	1937
dc.identifier.other	ARC/R&M-1838	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/1429
dc.description.abstract	Owing to improvements in aerodynamic design it is desirable to be able to predict profile drag accurately. A method of calculating the profile drag of aerofoils is developed and is applied to investigate the drag of a flat plate and of two aerofoils of different thicknesses for three Reynolds numbers and three transition point positions. From the results curves are drawn which show the variation of profile drag for a range of aerofoil thickness, Reynolds number and transition point position. Comparison with experimental results shows satisfactory agreement.	en_US
dc.language.iso	en	en_US
dc.publisher	H. M. Stationery Office	en_US
dc.relation.ispartofseries	Aeronautical Research Committee Reports & Memoranda	en_US
dc.title	The calculation of the profile drag of aerofoils	en_US
dc.type	Technical Report	en_US