Abstract
Grid generation techniques for unsteady finite wings and rotating blades with significant separation and dynamic stall analyses are largely based on infinite wing grid generation techniques, where span or radial spacing is considered of secondary importance to airfoil section spacing and can be large compared to the section longitudinal-normal spacing. An extensive finite wing planform mesh refinement, assessed for conditions where flow separation is present, indicates that there are recommended limits in the planform mesh aspect ratios related to the normal-chord cell aspect ratios, computed at the midchord location. The mesh recommendations have also been analyzed with respect to the accuracy provided by turbulence methods that are routinely applied today. These findings have been analyzed primarily for a translating wing but have been confirmed for a rotating system (rotor) with dynamic stall and separation present.
Published Version
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