Tests on a whirlwind aircraft in the royal aircraft establishment 24-ft wind tunnel (in two parts)

dc.contributor.author	T. V. Somerville	en_US
dc.contributor.author	R. R. Duddy	en_US
dc.contributor.author	G. H. L. Buxton	en_US
dc.date.accessioned	2014-10-21T15:51:45Z
dc.date.available	2014-10-21T15:51:45Z
dc.date.issued	1940	en_US
dc.identifier.other	ARC/R&M-2603	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/3140
dc.description.abstract	Tests were made in the 24-ft Wind Tunnel during March and April, 1940, on the Whirlwind aircraft to find if simple modifications can be introduced which will decrease its drag. The drag analysis is not complete and is focused chiefly on the drag due to leaks, cooling and excrescences. A complete record of the tests together with explanatory paragraphs is given in the tables of this note. The modifications which gave an appreciable saving in drag and which are considered possible to apply to the production aircraft are listed below.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Tests on a whirlwind aircraft in the royal aircraft establishment 24-ft wind tunnel (in two parts)	en_US