Implementation of MachLine: A Subsonic/Supersonic, Unstructured Panel Code

View Video Presentation: https://doi.org/10.2514/6.2023-1898.vid To meet the growing need for fast and accurate supersonic flow solutions, we present the implementation of a subsonic-supersonic, unstructured panel method. Novel results of this work include a source-free, Dirichlet boundary condition formulation, a streamlined approach to domain of dependence calculation on unstructured meshes, and some aspects of automatic supersonic wake modeling. We also present a complete method for calculating subsonic and supersonic influence coefficients. We examine the numerical behavior of the method and find it robust with respect to control point placement, mesh refinement, and mesh regularity. We also show the method is highly accurate for small-perturbation flows when compared to analytic results.