Abstract:
Part 1. Details of the Mathematical Techniques used in the Evaluation of the Pressure Distributions, and a Set of Numerical Results including Comparisons with Experiment. Details of a method which enables the calculation of converged pressure distributions on a wing with distorted control surfaces oscillating harmonically in linearised, compressible subsonic flow, are presented. The local loading solutions, which have been developed from the original work of Landahl are used to extract the discontinuous part of the boundary conditions associated with oscillating control surfaces. The resulting regularised problem is then solved using a Lifting Surface Collocation procedure, giving together with the local solutions, the required pressure distribution. Results using the current theory for a rectangular wing and two swept tapered wings, are compared with experiment and other theoretical methods, including the long established 'equivalent modes' technique.
