Fatigue test results and analysis of 42 piston provost wings

dc.contributor.author	H. E. Parish	en_US
dc.date.accessioned	2014-10-21T15:56:35Z
dc.date.available	2014-10-21T15:56:35Z
dc.date.issued	1965	en_US
dc.identifier.other	ARC/R&M-3474	en_US
dc.identifier.uri	https://reports.aerade.cranfield.ac.uk/handle/1826.2/4052
dc.description.abstract	The safe fatigue life of the Piston Provost was established by full-scale, programmed load, fatigue tests, the load spectrum being collected from 'in service' records. Forty 'life-expired' wings and an appropriate number of fuselages were used to continue the programmed load tests to failure with the object of determining the degree of scatter. A standard deviation of 0-087 and a coefficient of variation of 0.022 indicates less scatter than has been suggested in other literature. The estimated life obtained by using Miner's cumulative damage rule is compared with the mean of the experimental results.	en_US
dc.relation.ispartofseries	Aeronautical Research Council Reports & Memoranda	en_US
dc.title	Fatigue test results and analysis of 42 piston provost wings	en_US