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The Static Aeroelastic Deformation of Slender Configurations*

Part I: Some Elementary Concepts of Static Deformation

Published online by Cambridge University Press:  07 June 2016

G. J. Hancock
G. J. Hancock*
Affiliation:
Department of Aeronautical Engineering, Queen Mary College, University of London
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Summary

By consideration of a series of simple models the static aeroelasticity of conventional aircraft is first discussed and then extended to the integrated configuration combining fuselage, wing and tail. It is shown that, on the basis of linear aerodynamics, a maximum speed exists at which control is possible. Overall deformations and control forces become large at speeds approaching this critical condition. Part II, to be published, contains calculations on slender plate aircraft including non-linear aerodynamics.

Type
Research Article
Information
Aeronautical Quarterly , Volume 12 , Issue 3 , August 1961 , pp. 293 - 308
Copyright
Copyright © Royal Aeronautical Society. 1961

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References

1. Collar, A. R. The Expanding Domain of Aeroelasticity. Journal of the Roval Aeronauical Society, Vol. 50, August 1946.Google Scholar