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Solution of Aeroelastic Problems by Means of Influence Coefficients

Published online by Cambridge University Press:  28 July 2016

D. Williams
D. Williams*
Affiliation:
Royal Aircraft Establishment
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Summary

It is shown that, on the basis of the data provided by two sets of influence coefficients for a wing (or other surface)–an “elastic” set giving deflections (and hence incidence angles) in terms of applied loads, and an aerodynamic set giving aerodynamic loads in terms of incidence angles (or other linear function of the displacements)–all “static” aeroelastic problems can easily and expeditiously be solved by the use of a digital computer. It is also suggested that the same method of approach may well be used for solving oscillatory aeroelastic problems such as flutter.

Information

Type
Research Article
Information
The Aeronautical Journal , Volume 61 , Issue 556 , April 1957, pp. 247 - 251
Copyright
Copyright © Royal Aeronautical Society 1957

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References

1. Williams, D. (1954). Recent Developments in the Structural Approach to Aeroelastic Problems. Journal of the Royal Aeronautical Society, June 1954.CrossRefGoogle Scholar
2. Williams, D. (1954). A General Method (Depending on the Availability of a Digital Computer) for Deriving the Influence Coefficients of Aeroplane Wings. R.A.E. Report No. Structures 168, October 1954, also 209, May 1956. (Recommended for R. & M. Series.)Google Scholar
3. Frazer, R. A., Duncan, W. J. and Collar, A. R. (1938). Elementary Matrices. Cambridge University Press 1938.Google Scholar
4. Jones, W. P. (1947). Wing-Fuselage Flutter of Large Aeroplanes. R. & M. No. 2656, November 1947.Google Scholar