The pressure distribution, at supersonic speeds and zero lift, on some swept-back wings having symmetrical sections with rounded leading edges

dc.contributor.author	G. M. Roper	en_US
dc.date.accessioned	2014-10-21T15:52:23Z
dc.date.available	2014-10-21T15:52:23Z
dc.date.issued	1949	en_US
dc.identifier.other	ARC/R&M-2700	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3246
dc.description.abstract	Formulae are found for the pressure distribution at supersonic speeds and at zero incidence for certain symmetrical surfaces of small finite thickness, with swept-back leading edges, the surfaces being set symmetrically to the wind direction. The solutions are only valid if the surfaces lie wholly within the Mach cone of the apex.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	The pressure distribution, at supersonic speeds and zero lift, on some swept-back wings having symmetrical sections with rounded leading edges	en_US