Aerofoil theory of a flat delta wing at supersonic speeds

dc.contributor.author	A. Robinson	en_US
dc.date.accessioned	2014-10-21T15:56:17Z
dc.date.available	2014-10-21T15:56:17Z
dc.date.issued	1946	en_US
dc.identifier.other	ARC/R&M-2548	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3965
dc.description.abstract	Lift, drag, and pressure distribution of a triangular flat plate moving at a small incidence at supersonic speeds are given for arbitrary Mach number and aspect ratio. The values obtained for lift and drag are compared with the corresponding values obtained by strip theory. The possibility of further applications of the analysis leading up to the above results is indicated.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Aerofoil theory of a flat delta wing at supersonic speeds	en_US