Author(s)

L.C. Santos

Abstract

The development of any new design requires an extensive use of resources. During the preliminary design phase the changes of shape and subsequent analysis must be performed as fast as possible. The method of singularities, or panel method is still the fastest three-dimensional method of solution for potential flows and therefore is still widely used in the aerospace industry. This paper describes a ro- bust doublet based method that accurately describes the flow around the junction region. It allows the imbrication (intersection) of the separate components while computing the exact flow solution correspondent to the external surface. The in- tensity of all internal panels are automatically zero by the use of the doublets. To demonstrate its application the method is applied to compute wing-body interfer- ence coefficients for typical mi

Keywords