Hostname: page-component-cd9895bd7-gvvz8 Total loading time: 0 Render date: 2024-12-26T21:02:00.139Z Has data issue: false hasContentIssue false
  • English
  • Français

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
Get access

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.

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

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

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