A Higher-Order Panel Method for the Computation of the Flow About Slender delta Wings with Leading-Edge Vortex Separation

摘要

A second-order panel method for computing the limiting cases of conical flow about delta wings and time dependent two-dimensional development of the wake behind the trailing edge of wings is shown to be stable for the mixed design/analysis boundary conditions, characterizing both problems. The method for following two-dimensional vortex sheet motion includes an adaptive curvature dependent panel scheme and a concept for doubly-branched spiralling vortices, which enables the motion of vortex sheets of complicated shape to be followed up to large downstream distances. Conical flow results for different angles of attack and for different cross-sectional shapes are presented. Vortex sheet roll-up results for the wake behind a flat delta wing are presented. Results compare well with experiment and other model values.