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The Static Aeroelastic Deformation of Slender Configurations*

Part II: Some Calculations on Slender Plate Aircraft, Including Non-Linear Aerodynamics

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

Calculations have been applied to a series of flexible plates (delta, gothic and ogee) to estimate their static aeroelastic behaviour. Assuming linear aerodynamics, the general tendencies of Part I are particularised. Assuming non-linear aerodynamics, it is shown that in general two positions of equilibrium are apparently possible at each speed. The stability of the models is not considered.

Information

Type
Research Article
Information
Aeronautical Quarterly , Volume 12 , Issue 4 , November 1961 , pp. 372 - 394
Copyright
Copyright © Royal Aeronautical Society. 1961

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References

1. Hancock, G. J. Static Aeroelastic Distortion of Slender Configurations. Part I. Aeronautical Quarterly, Vol. XII, p 293, August 1961.CrossRefGoogle Scholar
2. Jones, R. T. Properties of Low Aspect Ratio Pointed Wings at Speeds Below and Above the Speed of Sound. N.A.C.A. Report 835,1946.Google Scholar
3. Mangler, L. W. and Snirra, J. H. A Theory of Flow past a Slender Delta Wing with Leading Edge Separation. Proc. Roy. Soc. A, 251, May 1959.Google Scholar
4. Maskell, E. C. and Weber, J. On the Aerodynamic Design of Slender Wings. Journal of the Royal Aeronautical Society, December 1959. 394 Google Scholar