A Comparison of Panel Methods for Subsonic Flow Computation

Abstract : Panel, or surface singularity, methods have been developed to the stage where they provide nominally exact numerical solutions for incompressible flow potential around complicated, real aircraft configurations. A large variety of these methods are in use or under development. This report provides a data base against which the various programs may be checked and makes comparisons of several methods with the datum solutions for several simple wing configurations and nacelle configurations. Datum results are from the Roberts (BAe) Spline-Naumann Program, and a pilot version of the Boeing Advanced Panel-Type Influence Coefficient Method. (Author)