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 (email@example.com) if you have any questions about the data.
LES of NACA4412 wing sections up to Rec=1 million
- 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.