Well-resolved LES of turbulent flow around a NACA4412 wing section

The databases on this page are publicly available. Please refer to the original publications when using the data.

Contact Ricardo Vinuesa (rvinuesa@mech.kth.se) if you have any questions about the data.

LES of NACA4412 wing sections up to Rec=1 million

Field
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).

Database

- 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).

- The data is stored in .mat format here.

- 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.