Flight Tests on "King Cobra" FZ.440 to investigate the Practical Requirements for the Achievement of Low Profile Drag Coefficients on a "Low Drag" Aerofoil

dc.contributor.author	F. Smith	en_US
dc.contributor.author	D. J. Higton	en_US
dc.date.accessioned	2014-10-21T15:53:35Z
dc.date.available	2014-10-21T15:53:35Z
dc.date.issued	1945	en_US
dc.identifier.other	ARC/R&M-2375	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3488
dc.description.abstract	This report describes measurements of profile drag made on the wing of the King Cobra aircraft, which has a low-drag profile of X.A.C.A. design. The profile drag was high with the original surface finish and although it was improved when the surface was polished the profile drag was still much too high for a low-drag aerofoil. By reduction of the surface waviness to ± one thousandth of an inch low drag coefficients of the order of 0.0028 were obtained. The report describes the technique used to reduce the waviness and also the effect of flies, dust, water, high Mach number and normal acceleration upon the low drag characteristics of the wing.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Flight Tests on "King Cobra" FZ.440 to investigate the Practical Requirements for the Achievement of Low Profile Drag Coefficients on a "Low Drag" Aerofoil	en_US