General Approach to Lifting-Line Theory, Applied to Wings with Sweep

Implementations of lifting-line theory predict the lift a finite wing using sheet semi-infinite vortices extending from vortex filament placed along locus aerodynamic centers wing. Prandtl’s classical implementation is restricted to straight wings in flows without side slip. In this Paper, it shown that can be extended swept if, at control points where induced velocity calculated, second derivative zero and trailing are perpendicular centers. Therefore, general presented conditionally forces each point joints such there segment lies Consideration given modeling section properties wings. The resulting formulation analyzed determine sensitivity closure parameters, accuracy, numerical convergence. demonstrates approximately second-order convergence when cosine clustered produces results closely match those higher-order panel method experimental data, though requiring only fraction computational cost.