The aerodynamic derivatives of an aerofoil oscillating in an infinite staggered cascade

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dc.contributor.authorCraven, A. H.
dc.date.accessioned2014-09-25T15:04:36Z
dc.date.available2014-09-25T15:04:36Z
dc.date.issued1960-01
dc.description.abstractThin aerofoil theory is used to obtain, in integral form the aerodynamic derivatives of an aerofoil oscillating in an infinite cascade. The theory allows for arbitrary stagger angle and phase difference between adjacent blades of the cascade. The expressions obtained reduce, for zero stagger and for in phase and antiphase oscillations, to known results.en_UK
dc.identifier.urihttp://dspace.lib.cranfield.ac.uk/handle/1826/8704
dc.language.isoenen_UK
dc.publisherCollege of Aeronauticsen_UK
dc.relation.ispartofseriesCollege of Aeronautics Reporten_UK
dc.relation.ispartofseries125en_UK
dc.relation.ispartofseriesCOA/125en_UK
dc.titleThe aerodynamic derivatives of an aerofoil oscillating in an infinite staggered cascadeen_UK
dc.typeReporten_UK

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