In this thesis, the surface-singularity method, now widely used over the world, is applied to solve the incompressible potential flow around aircraft-related three-dimensional geometries.
The governing equation, or the Laplacian eqn., is transformed to an integral form with the distribution of singularity strength over the body surface left as unknown.
Once the distribution of singularity strength is determined, the whole three-dimensional induced flow field is constructed from it by superposition.
The body surface is discretized into plane panels and they are distributed with panelwise-constant singularities.
A computer program is made, based on the panel method and is applied to a symmetric swept wing. Good comparison is obtained with existing data.
