An analysis of various alternative approaches in grid generation is presented. A grid-generation procedure for complex aircraft configurations could be based on a combination of three subprocesses, . decomposition of the flow domain into about 100 hexahedronal blocks, . trilineair transfinite interpolation to generate initial grid point distributions, and . elliptic mesh-size tuning and smoothing. To get insight into this procedure, mathematical models of these three subprocesses were worked out and analyzed. The results of the analysis are technical concepts required or desirable in the grid-generation procedure. These concepts are presented.