Two-dimensional airfoil tables play an important role in providing data for lower fidelity aerodynamic models. While this data is available for certain configurations, it may be necessary to model novel airfoil configurations. Existing rapid-analysis tools are limited to simple geometries and may make physical assumptions which do not hold for all flow conditions. Full CFD simulations typically require an expert user to spend considerable time meshing the airfoil. Handling multi-element airfoils using overset meshes introduces interpolation errors. The current work couples a strand/advancing front mesh generator in the near-body regions to an off-body unstructured mesh, to create a single mesh for the entire flow field. User effort is reduced by offering default meshing parameters based on best practices. The novelty of this method lies in the ability to identify line-structures in unstructured meshes, which is coupled to a Hamiltonian strand solver to compute the flow, using the full unsteady Navier-Stokes equations including a laminar/turbulent boundary layer transition model. Additionally, this solver can be used to run a large number of cases to generate airfoil tables and quantify effects of measurement uncertainty.
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