Dynamic aeroelasticity of aircraft with swept wings

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dc.contributor.authorRadok, J. R. M.
dc.date.accessioned2012-07-26T13:19:10Z
dc.date.available2012-07-26T13:19:10Z
dc.date.issued1952-04
dc.description.abstractUsing oblique coordinates, integro-differential equations of motion of aircraft with swept wings are deduced from Hamilton’s Principle for the dynamic problems of aero-elasticity, i.e. for the problems of free vibrations, flutter, dynamic stability and gust loads.en_UK
dc.identifier.urihttp://dspace.lib.cranfield.ac.uk/handle/1826/7432
dc.language.isoenen_UK
dc.publisherCollege of Aeronautics, Cranfielden_UK
dc.relation.ispartofseriesCollege Reporten_UK
dc.relation.ispartofseries58en_UK
dc.titleDynamic aeroelasticity of aircraft with swept wingsen_UK
dc.typeReporten_UK

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