Computation of Pressure Distribution on the DFVLR Wing-Body Model by the Panel Method

摘要

The panel method is based on a discrete singularity distribution. The complete surface of a given configuration is divided into a large number of plane quadrilateral or triangular panels and the singularity strength on each of these panels is obtained as a solution of an integral equation. A control point is selected on each panel in order to satisfy the boundary condition. Viscous effects are shown very important for supercritical wings having a large amount of rear loading, and the need to modify the panel method to include boundary layer calculations is highlighted.