Calculations of the lift slope and aerodynamic centre of cropped delta wings at supersonic speeds

dc.contributor.author	J. H. B. Smith	en_US
dc.contributor.author	J. A. Beasley	en_US
dc.contributor.author	A. Stevens	en_US
dc.date.accessioned	2014-10-20T11:02:48Z
dc.date.available	2014-10-20T11:02:48Z
dc.date.issued	1960	en_US
dc.identifier.other	ARC/CP-562	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/575
dc.description.abstract	The linearised theory of supersonic flow is used to calculate the lift slope and the aerodynamic centre of cropped delta wings which have subsonic leading edges. The cropped tip must be short enough for each tip to lie entirely upstream of the disturbances produced by the other. The results are prezented graphically and in brief tables.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Current Papers	en_US
dc.title	Calculations of the lift slope and aerodynamic centre of cropped delta wings at supersonic speeds	en_US