Measurements of skin friction on a cambered delta wing at supersonic speeds

dc.contributor.author	K. G. Winter	en_US
dc.contributor.author	K. G. Smith	en_US
dc.date.accessioned	2014-10-21T15:56:44Z
dc.date.available	2014-10-21T15:56:44Z
dc.date.issued	1965	en_US
dc.identifier.other	ARC/R&M-3501	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/4078
dc.description.abstract	Summary. The measurements, using razor blade surface pitot tubes, show that the relatively mild pressure gradients and streamline convergence on the wing have a large effect on local skin friction. Application of the boundary-layer momentum equation suggests that the change in skin friction arises directly from changes in the boundary-layer profile. Despite large variations the total skin-friction drag of the wing is within 10 per cent of that of a flat plate.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Measurements of skin friction on a cambered delta wing at supersonic speeds	en_US