| This thesis presents a new method of solution for the aerodynamics of finite-span wings, which overcomes the difficulties of the previous methods. The present method uses velocity singularities in the Trefftz plane (situated downstream at infinity) to derive the contributions in the solution of the circulation distribution caused by the changes in the spanwise variation of the wing chord and incidence. The new specific functions derived for these contributions contain both natural and forced symmetry and antisymmetry terms, and thus represent a correct mathematical modeling of the physical problem. The correct mathematical representation of these contributions leads to a highly accurate theoretical solution which is not the case in the previous methods.; The method has been validated in comparison with the results obtained by theoretical methods such as Rasmussen & Smith, and Carafoli for rectangular and tapered wings of uniform incidence, and with panel method (Katz & Plotkin) results. Accurate theoretical solutions have been derived for various wing geometries of aeronautical interest, such as wings with curved leading and trailing edges, and wings with asymmetric incidence variations caused by symmetric and antisymmetric deflection of flaps and ailerons (which are more difficult to model using the panel methods).; Furthermore, the present method of solution has been extended to solve the problem of swept wings. A procedure has been developed to specifically treat this problem. |
