NASA NTRS · 19910028644
Local grid refinement for transonic flow problems
Abstract
The present use of locally refined Cartesian grids to solve transonic flow problems about three-dimensional aircraft configurations obviates surface-conforming grid generation through an embedding of surface-geometry paneling in the grid. Accurate resolution of flow close to the boundary, and in regions with strong velocity gradients, is achieved via hierarchical local refinement which subdivides a given grid cell into eight cells. Fast and reliable convergence is obtained by combining several preconditioners and damping strategies. Methods are suggested for preclusion of global convergence problems.
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Melvin, Robin G., Bieterman, Michael B., Young, David P., Johnson, Forrester T., Samant, Satish S.. 1989-01-01. Local grid refinement for transonic flow problems. https://ntrs.nasa.gov/citations/19910028644
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