Wind tunnel tests at Mach numbers between 0.6 and 1.4 of a 60 degrees swept wing having an aerofoil section designed for subcritical flow at a Mach number of 1.2 part 1 9 percent thick section with "triangular" pressure distribution

dc.contributor.author	E. F. Lawlor	en_US
dc.date.accessioned	2014-10-20T11:03:08Z
dc.date.available	2014-10-20T11:03:08Z
dc.date.issued	1962	en_US
dc.identifier.other	ARC/CP-582	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/595
dc.relation.ispartofseries	Aeronautical Research Council Current Papers	en_US
dc.title	Wind tunnel tests at Mach numbers between 0.6 and 1.4 of a 60 degrees swept wing having an aerofoil section designed for subcritical flow at a Mach number of 1.2 part 1 9 percent thick section with "triangular" pressure distribution	en_US