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To meet the growing need for fast supersonic flow solutions, the theory and implementation of a modern subsonic/supersonic, unstructured panel method are here presented. This work presents several improvements over legacy supersonic panel codes and available modern codes. Among these improvements are automatic methods for generating unstructured wakes, enforcing the Kutta condition at trailing edges, and placing interior control points. An efficient method for calculating domains of dependence on an unstructured mesh is also presented. For the first time in the literature regarding supersonic panel methods, a complete method for calculating influence coefficients is also described. The numerical sensitivities of the method are examined. Compared to analytic and experimental data, the method is accurate for small-perturbation flows. For example, the relative error in the root pressure coefficient on a straight wing in supersonic flow (Formula: see text) was calculated to be within approximately 7% of the analytic solution for a range of angles of attack. For a delta wing in supersonic flow (Formula: see text), the method is found to calculate lift slope and zero-lift drag to within 5% of experimental data. The method is also fast, having run times on the order of 1 minute for meshes with around 26,000 panels.
Goates et al. (Sat,) studied this question.
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