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 |