  In this paper we present experimental and numerical reference data for a NACA
64A-110 airfoil at two angles of attack for $Ma=0.72$ and a Reynolds number of
$Re_c=930.000$ with respect to the chord length. The test cases are designed to
provide data for an uninclined airfoil at $0^\circ$ and for the case of a
stable, steady shock at $3^\circ$. For both cases we conduct experiments in the
trisonic wind tunnel at the RWTH Aachen including PIV data as well as numerical
wall-resolved large eddy simulations. The results show matching mean velocities
and Reynolds stresses in the wake and boundary layer region. The experiment
shows a stronger shock including a lambda structure, but the shock location and
the overall flow physics are in good agreement for the tested angles of attack.
The generated data can be used for code validation, feature development and
turbulence modeling.
