Measurements of maximum lift on 26 aerofoil sections at high mach number. Part I tests on 19 aerofoils. Part II Tests on a Further 7 Aerofoils

dc.contributor.author	J.A. Beavan et al	en_US
dc.date.accessioned	2014-10-21T15:52:17Z
dc.date.available	2014-10-21T15:52:17Z
dc.date.issued	1948	en_US
dc.identifier.other	ARC/R&M-2678	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3221
dc.description.abstract	The lift on a number of aerofoil sections mostly of 2-in. chord has been determined over a wide range of incidence and Mach number by measuring tile pressures on the walls of the 20 x 8 in. High Speed Tunnel. There is some evidence that the low Reynolds number of the tests is not important.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Measurements of maximum lift on 26 aerofoil sections at high mach number. Part I tests on 19 aerofoils. Part II Tests on a Further 7 Aerofoils	en_US