Grid-point requirements for large eddy simulation: Chapman’s estimates revisited

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Confinement effects in shock wave/turbulent boundary layer interactions through wall-modelled large-eddy simulations (2014, background): “For larger Reynolds numbers, the reduction in mesh size and associated computational cost resulting from the use of a wall model is increasingly significant (see, e.g., the estimates provided in Choi & Moin 2012).”
Enhancing computational fluid dynamics with machine learning (2021, background): “However, the ﬁne computational meshes required to resolve the smallest scales lead to exceedingly high computational costs, which increase with the Reynolds number [20].”
Importance of the nozzle-exit boundary-layer state in subsonic turbulent jets (2018, background): “Turbulent boundary layers are difficult to resolve in LES due to the substantial cost of simulating the full range of flow scales that are present (Choi & Moin 2012), to be added to the necessary cost of resolving the noise-source-containing region at least 15 diameters downstream of the nozzle…”
Aerodynamics of Heavy Vehicles (2014, background): “Chapman (1979) and Choi & Moin (2012) showed that the number of grid points required for the simulation of turbulent wall-bounded flow is significantly reduced when the near-wall dynamics is properly modeled and only a few grids are located near the wall.”