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Dynamic aeroelasticity of aircraft with swept wings

By J. R. M. Radok

Abstract

Using 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

Publisher: College of Aeronautics, Cranfield
Year: 1952
OAI identifier: oai:dspace.lib.cranfield.ac.uk:1826/7432
Provided by: Cranfield CERES

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