A general method (depending on the aid of a digital computer) for deriving the structural influence coefficients of aeroplane wings Parts 1 and 2

Abstract

A general method (requiring the aid of a digital computer) is described for deriving the influence coefficients of any type of wing, and hence for evaluating its strength and stiffness characteristics. The method allows for shear deflections, and hence implicitly takes account of effects like shear lag and warping of wing cross-sections. A rapid method accurate enough to serve as a basis for dynamical calculations is first described, and secondly a more rigorous method on which to base final stressing of the structure. In Part I a method for deriving the influence coefficients of any type of wing, and hence of deriving the deflection and stresses, was described in outline. The practical application of the method, however, raises a number of minor problems (mostly concerned with boundary values), which have all to be overcome if the method is to become popular among stressmen. Some of the more important of these problems are treated in this part.