Abstract
SummaryIt 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.
Publisher
Cambridge University Press (CUP)
Reference4 articles.
1. 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.)
2. Jones W. P. (1947). Wing-Fuselage Flutter of Large Aeroplanes. R. & M. No. 2656, November 1947.
3. Recent Developments in the Structural Approach to Aeroelastic Problems
4. Elementary Matrices