LES of NACA4412 wing sections up to Rec=1 million

Coherent vortical structures for the four well-resolved LESs at (from left to right) Rec=100k, 200k, 400k and 1 million.
Figure extracted from Vinuesa et al., Int. J. Heat Fluid Flow 72 (2018).


The database is described in: R. Vinuesa, P. S. Negi, M. Atzori, A. Hanifi, D. S. Henningson and P. Schlatter. Turbulent boundary layers around wing sections up to Rec = 1,000,000. Int. J. Heat Fluid Flow, 72, 86-99 (2018).

The local edge velocity (Ue) and 99% boundary-layer thickness (delta99) were calculated using the method in: R. Vinuesa, A. Bobke, R. Orlu and P. Schlatter. On determining characteristic length scales in pressure-gradient turbulent boundary layers. Phys. Fluids, 28, 055101 (2016).

All the turbulence statistics are expressed in the local tangential and wall-normal frame of reference, with the proper tensor rotations.

The data is organized into Matlab structures, where each entry is a streamwise position.

The variables top and bottom refer to the suction and pressure sides, respectively. The number refers to the Reynolds number, where 1 is 100k and 10 is 1 million.

The variables x and y indicate the position of the profile points in the global frame of reference. The variables xa and ya denote the position at the airfoil.

The variable yn refers to the wall-normal profile, starting with 0 at the wall.

The database includes mean flow, Reynolds-stress tensor, integral quantities and turbulent kinetic energy budget terms.

LES of NACA0012 wing section at Rec=400,000

Coherent vortical structures for the well-resolved LES at Rec=400k.
Figure extracted from Tanarro, Vinuesa and Schlatter, J. Fluid Mech. 883 (2020).


The database is described in: A. Tanarro, R. Vinuesa and P. Schlatter. Effect of adverse pressure gradients on turbulent wing boundary layers. J. Fluid Mech. 883, A8, (2020).

The provided statistics exploit the symmetry of the flow.

Same format and considerations as in the NACA4412 database.