Analysis of the static pressure distribution on a delta wing in subsonic flow

dc.contributor.author	D. L. I. Kirkpatrick	en_US
dc.date.accessioned	2014-10-21T15:50:10Z
dc.date.available	2014-10-21T15:50:10Z
dc.date.issued	1968	en_US
dc.identifier.other	ARC/R&M-3619	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/2886
dc.description.abstract	The static-pressure distribution on the surface of a thin delta wing of aspect ratio 1.616 was measured at several incidences in subsonic flow, and the results were analysed to investigate the development with incidence of the leading-edge vortices above the wing and of the chordwise distribution of the aerodynamic loading on it. The results were compared with those obtained from ealier tests to demonstrate how the chordwise distribution of aerodynamic loading on a slender wing is affected by its aspect ratio, thickness and wing-tip shape.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Analysis of the static pressure distribution on a delta wing in subsonic flow	en_US