Aileron Reversal and Divergence of Swept Wings with Special Consideration of the Relevant Aerodynamic and Elastic Characteristics

Abstract

Using oblique coordinates, the static problems of Aero-elasticity for swept wings are reduced to the solution of integral - or matrix equations, which may be solved by iteration. The present treatment also indicates the suitability of integral equations for fundamental aero-elastic investigations. It shows that the ab initio use of matrix equations may lead to more complicated calculations, and that for this reason they should be confined to computation offices, particularly since the transition from the integral equations to the matrix equations mostly used in this type of work requires only a simple formal transformation. Application of the theory to a simple swept wing is given and its divergence speed obtained. In two Appendices methods are deduced for estimating the aerodynamic derivatives and calculating the elastic influence functions from experimental data. Both methods are applied to the case of a model wing, and the influence functions thus obtained are compared with their theoretical values. To simplify future applications of this method, the complete calculations are presented in the form of tables, suitable as computation schemes. The College of Aeronautics was founded in 1946 and was granted university status in 1969 becoming the Cranfield Institute of Technology. In 1993 it changed its name to Cranfield University.