Vortex sheet modeling with higher order curved panels

A method to predict the shape of the vortex sheet in the vicinity of its generating lifting surface is presented. The method uses potential flow vortex panels with a bilinear vorticity distribution and bicubic position interpolant to enable continuity to the necessary order. Positions of the panel nodes of successive streamwise stations are iteratively updated using the induced velocities computed from the sheet's configuration during the previous cycle. Complex wing loadings can be used, such as the case of deployed partial span flaps, or stalled conditions. However, the spanwise node density must be adjusted accordingly. Good correlation was obtained for a simply loaded wing tested in the Boeing Company Research Wind Tunnel, and the results show a considerable improvement over current methods of prediction which use discrete vortex filaments. Such a method would be useful in predicting certain stability derivatives in various flight regimes, as well as in the evaluation of the induced effects on other aircraft surfaces.