Summary
The prediction of aerodynamic drag for complex configurations using CFD is a nontrivial matter. The computed drag is affected by numerical discretization and physical modelling error. The discretization error due to the finite computational grid can be estimated by grid extrapolation techniques. Aerodynamic coefficients can be extrapolated to within 1 of the grid independent value using a grid refinement approach. The GCI can be between 5 - 15 for lift and drag. Reliable evaluations of grid-independent solutions and error bands require high-quality grids on all levels of grid convergence studies.
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Rakowitz, M. (2002). Grid Refinement Study with a UHCA Wing-Body Configuration Using Richardson Extrapolation and Grid Convergence Index GCI. In: Wagner, S., Rist, U., Heinemann, HJ., Hilbig, R. (eds) New Results in Numerical and Experimental Fluid Mechanics III. Notes on Numerical Fluid Mechanics (NNFM), vol 77. Springer, Berlin, Heidelberg. https://doi.org/10.1007/978-3-540-45466-3_36
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DOI: https://doi.org/10.1007/978-3-540-45466-3_36
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