Numerical simulation of leading-edge vortex flow
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Abstract
An analysis is presented of results of a computational method to simulate the steady compressible vortical type of flow around a 65-deg sharp-edged cropped delta wing. The discussion emphasizes some more fundamental aspects of the numerical simulation such as the separation of the flow, the structure of the leading-edge vortex core and the flow inside the free shear layer closed-form solutions are presented which might assist in the analysis of the numerical results.