Abstract
The flexibility required to construct computational grids around aircraft configurations has led to the development of the multiblock or composite grid approach. This technique requires the flow domain to be subdivided into blocks, the arrangement of which defines the topology of the grid. Here, a multiblock grid generation procedure is presented that is capable of constructing grid topologies that are locally consistent with the geometrical topology of each component of the configuration. An automatic method of subdividing the flow domain into blocks has been developed. This procedure has been interfaced with a method of grid control that ensures that the grids generated have a suitable grid point distribution. The method is flexible and is applicable to all components of an aircraft configuration. Illustrations of the use of the method are presented, including application to a wing-fuselage-foreplane-pylon-store geometry. The suitability of such grids for flow calculations is demonstrated by presenting results from an algorithm used to solve the Euler equations.
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