A new panel arrangement, orthogonal at the leading edge and adapted to the resulting low at the trailing edge, is implemented in a boundary element method/or the analysis of propeller tip flows. This panel arrangement is found to improve: (a) the accuracy of the predicted velocity flow field and pressure distribution at the tip region, and (b) the numerical performance of the boundary element method.

This content is only available via PDF.
You can access this article if you purchase or spend a download.