Tests on a swept-back wing and body in the compressed air tunnel

dc.contributor.author	C. Salter	en_US
dc.contributor.author	C. J. W. Miles	en_US
dc.contributor.author	H. M. Lee	en_US
dc.date.accessioned	2014-10-21T15:52:35Z
dc.date.available	2014-10-21T15:52:35Z
dc.date.issued	1950	en_US
dc.identifier.other	ARC/R&M-2738	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3286
dc.description.abstract	The model consisted of a swept-back wing of symmetrical section and a long cylindrical body. The aspect ratio was 3.29, the taper ratio 2.75, the sweep of the quarter-chord line 42.5 deg, the maximum thickness/chord ratio at the root 8.6 per cent and at the tip 10 per cent. It has been tested over a range of Reynolds numbers of 0.5 x 10power66 to 13 x 10power6 and results are given of lift, drag and pitching moment for angles of incidence up to 30 deg.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Tests on a swept-back wing and body in the compressed air tunnel	en_US