Some effects of Reynolds number on a cambered wing at high subsonic Mach numbers

dc.contributor.author	H.E. Gamble	en_US
dc.date.accessioned	2014-10-20T11:00:09Z
dc.date.available	2014-10-20T11:00:09Z
dc.date.issued	1951	en_US
dc.identifier.other	ARC/CP-103	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/116
dc.description.abstract	An untapered, sweptback wing of aspect ratio 4, sweepback 25 degrees and section 12% thick (R.A.E. 104 with 1% camber, a = 0.6) was tested in the R.A.E. Hqh Speed Tunnel. The pressure distribution was measured at the mid-semispan section at various Mach numbers up to 0.88 at Reynolds numbers of 0.8, 1.8 and 3.5 x 10 to the power 6.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Current Papers	en_US
dc.title	Some effects of Reynolds number on a cambered wing at high subsonic Mach numbers	en_US