Calculation of the effect of slipstream on lift and induced drag. Part 1. Wing of infinite span

dc.contributor.author	Aeronautical Research Council	en_US
dc.date.accessioned	2014-10-21T15:53:31Z
dc.date.available	2014-10-21T15:53:31Z
dc.date.issued	1945	en_US
dc.identifier.other	ARC/R&M-2368	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3477
dc.description.abstract	The lift distribution along a wing of infinite span with a central jet of higher velocity is calculated by standard methods of aerofoil theory for several values of (jet velocity/stream velocity) and of (jet diameter/wing chord). The lift increment and the induced drag are determined and the application of the results to practical cases is discussed.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Calculation of the effect of slipstream on lift and induced drag. Part 1. Wing of infinite span	en_US