Abstract
In the present study, two codes that solve the three-dimensional thin-layer Navier-Stokes (TLNS) equations are used to compute the steady-state flow for two test cases representing typical finite wings at transonic conditions. The first code, CFL3D, uses an implicit upwind-biased scheme, while the second, TLNS3D, uses an explicit central-difference scheme. Comparisons of computed surface pressure distributions with experimental data and analysis of global aerodynamic coefficient data indicate that for a given grid, CFL3D is more accurate, while TLNS3D is more efficient. To achieve the same level of accuracy, TLNS3D requires more grid points than CFL3D, but converges using slightly less computer time.
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