A-airfoil

In several of our papers the Aerospatiale airfoil, the A-aifoil has been computed by LES.
See

[C.P. Mellen, J. Fröhlich, W. Rodi. AIAA J., 41:573-581, 2003]

[ L. Davidson et al. (eds). LESFOIL: Large Eddy Simulation of Flow Around a High Lift Airfoil Notes on Numerical Fluid Mechanics, vol. 83, Springer, 2003. ]


We have been asked repeatedly for the geometrical data describing the profile.
This data can be downloaded here for the upper side and the lower side.

Several computations have been performed with a blunt trailing edge. This was motivated by the fact that the experiments also were conducted with a profile featuring a blunt trailing edge. The previous RANS computations were performed with a sharp trailing edge. The geometry for the blunt edge is obtained by modifying the lower boundary as follows. Starting from x/c=0.4, the point of maximum thickness, the lower wall is shifted downwards (linearly increasing with x) such that a blunt trailing edge of thickness 0.005 c is created. (see the above references).


The experimental data for comparison can be obtained here.