Three-Dimensional Flow over Wings with Leading-Edge Vortex Separation

Recent advances in a panel method for the solution of three-dimensi onal flow about wing and wing-body combinations with leading-edge vortex separation are presented. These advances were achieved as par't of an ultimately successful assault on two shortcomings of the method, namely convergence failures in seemingly random cases, and overprediction of lift coefficient for high aspect-ratio wings. Advances include the implementation of improved panel numerics for the purpose of eliminating the highly nonlinear effects of ring vortices around doublet panel edges, and the development of a least-squares procedure for damping vortex sheet geometry update instabilities. A variety of cases generated by the computer program implementing the method are presented. These cases are of two types. The first type consists of numerical studies, which verify the underlying mathematical assumptions of the method and moreover show that the results are strongly invariant with respect to such user dependent input as wing panel layout, initial sheet shape, sheet rollup, etc. The second type consists of cases run for the purpose of comparing computed results with experimental data, and these comparisons verify the underlying physical assumptions made by the method. a A & b B c CD Q

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