Abstract
Drag predictions of the DLR-F6 wing body, with and without the FX2B fairing, are demonstrated using both structured and unstructured grid solvers. The ability to accurately predict incremental drag is key to drag-based design and optimization. The focus of this study was to demonstrate drag and grid convergence on the two configurations. Analyses of the F6 configurations were based on the structured Navier-Stokes code, CFL3D, and on two unstructured Navier-Stokes codes, BCFD and CFD + +. Drag and grid convergence characteristics, drag polars, and pressure distribution for the configurations are presented. Results illustrate the use of a mature, structured-grid generator and solver compared to the use of two new-technology, unstructured grid generators and solvers.
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